From 1d961310094565015edb6feca00eea0abcf00a78 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 08:57:42 -0600 Subject: [PATCH 01/11] Move docs around so literate examples are in the examples folder, update installation documentation --- README.md | 6 +- docs/OWENS.code-profile | 1 + docs/generate.jl | 2 +- docs/make.jl | 4 +- docs/setup/OWENS_Julia_VS.code-profile | 1 - docs/setup/setup_HPWS.sh | 48 - docs/setup/setup_mac.sh | 44 - docs/src/assets/OWENS_Processes.png | Bin 0 -> 291370 bytes docs/src/index.md | 19 +- docs/src/{setup.md => installation.md} | 38 +- docs/src/literate/airfoils/Airfoils.txt | 39 - docs/src/literate/airfoils/NACA_0015.dat | 1379 ---------------- .../src/literate/airfoils/NACA_0015_RE3E5.dat | 130 -- .../src/literate/airfoils/NACA_0018_AllRe.dat | 1464 ----------------- docs/src/literate/airfoils/NACA_0021.csv | 37 - docs/src/literate/airfoils/NACA_0021.dat | 1211 -------------- .../literate/airfoils/NACA_0021_p2_53perc.csv | 37 - docs/src/literate/airfoils/SNL_0018_50.csv | 63 - .../literate/airfoils/SNL_0018_50_p7perc.csv | 63 - docs/src/literate/airfoils/Sandia_001850.dat | 845 ---------- docs/src/literate/airfoils/TUD_42.csv | 178 -- docs/src/literate/airfoils/e212-il.csv | 62 - docs/src/reference/reference.md | 2 +- examples/SNL34m/SNL34m_Inputs.yml | 2 +- examples/SNL34m/figs/.gitignore | 1 + .../dev/airfoils/NACA_0018.txt | 0 .../literate/A_simplyRunningOWENS.jl | 4 +- .../literate/B_detailedInputs.jl | 5 +- .../literate/C_customizablePreprocessing.jl | 2 +- examples/literate/airfoils/NACA_0018.txt | 208 +++ .../literate/airfoils/circular.csv | 0 ..._5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv | 42 +- .../NuMAD_Geom_SNL_5MW_D_TaperedTower.csv | 0 .../data/NuMAD_Geom_SNL_5MW_Struts.csv | 8 +- .../literate/data/NuMAD_Materials_SNL_5MW.csv | 0 .../src => examples}/literate/sampleOWENS.yml | 6 +- 36 files changed, 288 insertions(+), 5663 deletions(-) create mode 100644 docs/OWENS.code-profile delete mode 100644 docs/setup/OWENS_Julia_VS.code-profile delete mode 100644 docs/setup/setup_HPWS.sh delete mode 100644 docs/setup/setup_mac.sh create mode 100644 docs/src/assets/OWENS_Processes.png rename docs/src/{setup.md => installation.md} (80%) delete mode 100644 docs/src/literate/airfoils/Airfoils.txt delete mode 100644 docs/src/literate/airfoils/NACA_0015.dat delete mode 100644 docs/src/literate/airfoils/NACA_0015_RE3E5.dat delete mode 100644 docs/src/literate/airfoils/NACA_0018_AllRe.dat delete mode 100644 docs/src/literate/airfoils/NACA_0021.csv delete mode 100644 docs/src/literate/airfoils/NACA_0021.dat delete mode 100644 docs/src/literate/airfoils/NACA_0021_p2_53perc.csv delete mode 100644 docs/src/literate/airfoils/SNL_0018_50.csv delete mode 100644 docs/src/literate/airfoils/SNL_0018_50_p7perc.csv delete mode 100644 docs/src/literate/airfoils/Sandia_001850.dat delete mode 100644 docs/src/literate/airfoils/TUD_42.csv delete mode 100644 docs/src/literate/airfoils/e212-il.csv create mode 100644 examples/SNL34m/figs/.gitignore rename docs/src/literate/airfoils/NACA_0018_Coords.txt => examples/dev/airfoils/NACA_0018.txt (100%) rename {docs/src => examples}/literate/A_simplyRunningOWENS.jl (86%) rename {docs/src => examples}/literate/B_detailedInputs.jl (98%) rename {docs/src => examples}/literate/C_customizablePreprocessing.jl (99%) create mode 100644 examples/literate/airfoils/NACA_0018.txt rename {docs/src => examples}/literate/airfoils/circular.csv (100%) rename {docs/src => examples}/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv (76%) rename {docs/src => examples}/literate/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv (100%) rename {docs/src => examples}/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv (84%) rename {docs/src => examples}/literate/data/NuMAD_Materials_SNL_5MW.csv (100%) rename {docs/src => examples}/literate/sampleOWENS.yml (94%) diff --git a/README.md b/README.md index ebabaece..6105900d 100644 --- a/README.md +++ b/README.md @@ -4,9 +4,9 @@ ![](https://github.com/sandialabs/OWENS.jl/workflows/CI/badge.svg) -This package was based on the original structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). However, it has been rewritten into the Julia programming language and many of the issues related to aerodynamic coupling and floating dynamics solved, with extensive expansion into other areas and features to provide a seamless and automated process that takes in high level design details and does all of the preprocessing, running, and post processing that is normally done under different roofs or by different manual processes. This was done with the intent of enabling fast, parametric design. We have many of the modules propogating automatic gradients, however this is still a future challenge to solve well. +This package is for experienced researchers and analyists with both software and engineering experience who need generalized flexibility and performance that is 100% open source and is compatible with gradient based optimization with automatic gradients in process. If you want a windows compatible GUI, please use QBlade. -This package is for experienced researchers with both software and engineering experience who need generalized flexibility and performance that is 100% open source. If you want a windows compatible GUI, please use QBlade from our friends across the pond. +OWENS is an ontology, or way of coupling modular aerodynamic, structural, hydrodynamic, and controls packages. It was originally based on the structural dynamics solver by Brian Owens (see dissertation: http://hdl.handle.net/1969.1/151813). However, it has been rewritten into the Julia programming language, modularized, and many of the issues related to aerodynamic coupling and floating dynamics solved, with extensive expansion into other areas and features to provide a seamless and automated process that takes in high level design details and does all of the preprocessing, running, and post processing that is normally done under different roofs or by different manual processes. This was done with the intent of enabling fast, parametric design. We have many of the modules propogating automatic gradients, however this is still a future challenge to solve well. Here are several examples of OWENS use cases, current and past, including the Sandia 34m research turbine. @@ -53,7 +53,7 @@ Please follow the instructions on the setup page in the documentation. - All of the functions have docstrings describing the i/o and function purpose, which can be accessed the docs site or by: * import module * ? module.function() -- A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane. +- A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane, or by optionally loading the provided VS code profile in the OWENS.jl/docs folder. 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\ No newline at end of file diff --git a/docs/generate.jl b/docs/generate.jl index 17bee9b2..8d8d7f7f 100644 --- a/docs/generate.jl +++ b/docs/generate.jl @@ -3,7 +3,7 @@ import Literate is_ci = haskey(ENV, "GITHUB_ACTIONS") -EXAMPLEDIR = joinpath(@__DIR__, "src", "literate") +EXAMPLEDIR = joinpath(@__DIR__, "../examples", "literate") GENERATEDDIR = joinpath(@__DIR__, "src", "examples") mkpath(GENERATEDDIR) diff --git a/docs/make.jl b/docs/make.jl index ad09cd3b..1031a942 100644 --- a/docs/make.jl +++ b/docs/make.jl @@ -8,14 +8,14 @@ makedocs(; modules = [OWENS], pages = [ "Home" => "index.md", - "Installation" => "setup.md", + "Installation" => "installation.md", "Examples" => [ joinpath("examples", "A_simplyRunningOWENS.md"), joinpath("examples", "B_detailedInputs.md"), joinpath("examples", "C_customizablePreprocessing.md"), ], "Developer Guide" => "OWENS_Dev_Guide.md", - "Frames of Reference" => "FramesOfReference.md", + # "Frames of Reference" => "FramesOfReference.md", "API Reference" => joinpath("reference", "reference.md"), "Legacy User Guide" => "legacyUserGuide.md", "Legacy VAWTGen Guide" => "VAWTGenUserGuide.md", diff --git a/docs/setup/OWENS_Julia_VS.code-profile b/docs/setup/OWENS_Julia_VS.code-profile deleted file mode 100644 index 0352a466..00000000 --- a/docs/setup/OWENS_Julia_VS.code-profile +++ /dev/null @@ -1 +0,0 @@ -{"name":"OWENS","settings":"{\"settings\":\"{\\n \\\"terminal.integrated.commandsToSkipShell\\\": [\\n \\\"language-julia.interrupt\\\"\\n ],\\n \\\"julia.symbolCacheDownload\\\": true,\\n \\\"julia.enableTelemetry\\\": false,\\n \\\"editor.multiCursorModifier\\\": \\\"ctrlCmd\\\",\\n \\\"workbench.colorTheme\\\": \\\"Atom One Dark\\\",\\n \\\"diffEditor.ignoreTrimWhitespace\\\": false,\\n \\\"explorer.confirmDelete\\\": false,\\n \\\"julia.enableCrashReporter\\\": false,\\n \\\"julia.execution.saveOnEval\\\": true,\\n \\\"files.associations\\\": {\\n \\\"*.jl\\\": \\\"julia\\\"\\n },\\n \\\"julia.additionalArgs\\\": [\\n \\n 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hydrodyn_c_binding -make aerodyn_inflow_c_binding -make aerodyn_driver -make turbsim -cd ../../ - -julia -e 'using Pkg;Pkg.develop(url="../../GXBeam.jl")' - -# Add registered packages for running the example scripts -julia -e 'using Pkg;Pkg.add("PyCall");ENV["PYTHON"] = "/projects/struct_mech_tools/bin/python3.9/bin/python"; - Pkg.add("PyPlot");Pkg.add("Statistics");Pkg.add("DelimitedFiles");Pkg.add("Dierckx");Pkg.add("QuadGK");Pkg.add("FLOWMath"); - Pkg.add("HDF5")' - -# Install OWENS and non-registered dependencies as a regular user -julia -e 'using Pkg; Pkg.add(PackageSpec(url="https://github.com/byuflowlab/Composites.jl.git")); Pkg.add(PackageSpec(url="git@cee-gitlab.sandia.gov:8921-VAWT-TOOLS/OWENSPreComp.jl.git")); Pkg.add(PackageSpec(url="git@cee-gitlab.sandia.gov:8921-VAWT-TOOLS/OWENSOpenFASTWrappers.jl.git")); Pkg.add(PackageSpec(url="git@cee-gitlab.sandia.gov:8921-VAWT-TOOLS/OWENSAero.jl.git")); Pkg.add(PackageSpec(url="git@cee-gitlab.sandia.gov:8921-VAWT-TOOLS/OWENSFEA.jl.git")); Pkg.add(PackageSpec(url="git@cee-gitlab.sandia.gov:8921-VAWT-TOOLS/OWENS.jl.git"))' - -using PyCall -pygui(:qt5) -using PyPlot - - -# Run the example script -julia -e 'using PyCall; pygui(:qt5); include("ExampleSNL5MW_turbulent.jl")' - -#for VPM -#module load sparc-dev/intel-2021.3.0_mpich2-3.2 -# follow ed's instructions, but must remove compat for CXXWrap, run update in julia, and then dev . for FLOWExaFMM -# clone GXBeam, remove implicitAD compat, add main ImplicitAD, dev GXBeam \ No newline at end of file diff --git a/docs/setup/setup_mac.sh b/docs/setup/setup_mac.sh deleted file mode 100644 index 7e041706..00000000 --- a/docs/setup/setup_mac.sh +++ /dev/null @@ -1,44 +0,0 @@ - -#!/usr/bin/env bash - -# This script assumes you already have the required ssh keys and proxy (if needed) all set up. -# Also assumes you have the necessary fortran compilers -# xcode-select -install -# brew install cmake 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Note that arbitrary numbers of struts can be specified in the automatic meshing functions. You can also write your own generalized mesh using the internal building blocks, but it is not thouroughly documented. -drawing +drawing The generalized meshing was modified to include HAWT concepts, like this bi-wing concept. OWENS is capable of axial flow turbines/HAWTs, but it is not a mature feature, and no where near as developed as OpenFAST (i.e. for regular HAWTs it is recommended to use that software). -drawing +drawing Then, floating turbines are a possibility, though this feature adds another dimension to the nonlinear time stepping convergance and in turn a fair amount of time. Future work is to make this general interface and functionality an easy to use feature (right now it needs a high level of experience to use). -drawing +drawing # OWENS under the hood @@ -41,6 +44,8 @@ Turbulent inflow is provided by OWENSOpenFASTWrappers.jl and the inflowwind and Rainflow counting was provided by Rainflow.jl, however, this package became orphained and was pulled into the OWENS code base. +drawing + ## Installation Please follow the instructions on the setup page @@ -49,7 +54,7 @@ Please follow the instructions on the setup page - All of the functions have docstrings describing the i/o and function purpose, which can be accessed the docs site or by: * import module * ? module.function() -- A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane. +- A note about julia debuggers – if you don’t want it to step through everything, you need to tell it what packages to compile vs while packages to step through. This will make the debugger comparable (if not faster) than Matlab in speed. In VSCode, this can be done in the debug pane, or by optionally loading the provided VS code profile in the OWENS.jl/docs folder. This VS code profile will also set up the julia environment and other useful packages and key bindings, and can be modified as desired. ## Software License diff --git a/docs/src/setup.md b/docs/src/installation.md similarity index 80% rename from docs/src/setup.md rename to docs/src/installation.md index 4c286a55..6b25ad44 100644 --- a/docs/src/setup.md +++ b/docs/src/installation.md @@ -1,29 +1,38 @@ # Installation Instructions -The OWENS software has been developed and designed to operate in the paradigm similar to modern open source software, leveraging tools such as the terminal, git, public software repositories, and automated package management both for the operating system and the programming language. Before attempting these instructions, if you are not familiar with these types of tools, please consider becoming familiar with them prior to proceeding. Here are some of the first google hits for guides: +The OWENS software has been developed and designed to highly flexible and to operate in the paradigm similar to modern open source software, leveraging tools such as the terminal, git, public software repositories, and automated package management both for the operating system and the programming language. Before attempting these instructions, if you are not familiar with these types of tools, please consider becoming familiar with them prior to proceeding. Here are some of the first google hits for guides: - https://www.redhat.com/sysadmin/beginners-guide-vim - https://www.freecodecamp.org/news/the-beginners-guide-to-git-github/ - https://www.howtogeek.com/63997/how-to-install-programs-in-ubuntu-in-the-command-line/ +In short, you should be able to compile OpenFAST on your system before attempting this. Future distributions are planned to also include a precompiled binary for each of the three major operating systems, with the aspiration of being able to reduce the required knowledge to the OWENS inputs, outputs, and operation. Until then, here are installation instructions for the three major operating systems. **ORDER OF OPERATIONS AND DETAILS ARE IMPORTANT FOR A SUCCESSFUL BUILD, DO NOT SKIP STEPS** ## Windows -At this stage in the software's maturity, it is recommended to use mac or linux environments unless the user is experienced with compiled software development in a windows environment. The WSL (windows subsystem for linux) can also be installed (https://allthings.how/how-to-use-linux-terminal-in-windows-11/) and can be set up to run via just the terminal or also set up to use the graphical capabilities of your machine, and the memory can be mapped back and forth as described in the link above. +At this stage in the software's maturity, please use mac or linux environments unless the user is **highly** experienced with compiled software development in a windows environment. Installation and troubleshooting on a dedicated unix based system is at least 1/10th that of Windows (also why every supercomputer uses linux...) The WSL (windows subsystem for linux) can also be installed (https://allthings.how/how-to-use-linux-terminal-in-windows-11/) and can be set up to run via just the terminal or also set up to use the graphical capabilities of your machine, and the memory can be mapped back and forth as described in the link above. However, this adds several levels of complexity, and you **WILL** run into machine based issues until we finish the pipeline for windows download and run precompiled binaries. -Install julia, paraview, and visual studio manually by downloading the windows executables for +Install julia, paraview, and visual studio manually by downloading/installing the windows versions for each: - https://julialang.org/downloads/ - https://www.paraview.org/download/ - https://visualstudio.microsoft.com/downloads/ -Also download OpenFAST: -- https://github.com/OpenFAST/openfast -Be sure julia is on your path, and follow the windows compilation instructions for the openfast Inflowwind, AeroDyn, MoorDyn and HydroDyn libraries. Installation is otherwise the same as the Linux instructions below +When setting up ssh keys, be sure to follow the windows specific instructions https://docs.github.com/en/authentication/connecting-to-github-with-ssh/generating-a-new-ssh-key-and-adding-it-to-the-ssh-agent and note that you may have to use id_ecdsa keys. + +Set up the environment variables below and be sure Julia is also on the path (https://www.wikihow.com/Create-an-Environment-Variable-in-Windows-10) + +Install the OWENS custom dependices as listed below. + +If you wish to use the openfast libraries, follow the windows compilation instructions for the openfast Inflowwind, AeroDyn, MoorDyn and HydroDyn libraries. Also note that you will need to change the library paths in the top level OWENS scripts to match the resulting libraries' locations. + +Set up VS code as also described below. + +Windows notes: details are key, hash mismatch may mean that you are behind a proxy and the proxy isn't setup correctly. For visual studio, the default installation and recommendations should work. If importing the provided vs-code profile, the quick keys may need to be remapped to control from cmd. ## Mac @@ -64,7 +73,7 @@ Additionally, if you are not finding that your path is being appended to, you ca alias julia="path/to/your/julia-1.x.x/bin/julia" -# Proxy Setup +# Environment Variables If you are using a proxy, be sure that the proxy variables are declared/exported in your .bash_profile or .bashrc or the equivalent http_proxy, https_proxy, HTTP_PROXY, HTTPS_PROXY, no_proxy, NO_PROXY @@ -105,6 +114,7 @@ Additionally, if you find that your ssh is erroring when you try to install pack PubkeyAcceptedAlgorithms +ssh-ed25519 # Install Optional OpenFAST Dependices +If your system is already set up such that it is capable of compiling OpenFAST, and you are on mac or linux, then you may skip this and rely on the automatically compiled version that are created when the OWENSOpenFAST libraries are installed by Julia. mkdir coderepos cd coderepos # Install openfast coupled libraries !NOTE!: if you change the location of the compiled libraries, you may need to update the rpath variable, or recompile. @@ -298,7 +308,7 @@ rm("delim_file.txt") # julia's function that does the same thing ``` ## OWENS Installation -These steps require privileges to each package through github. This should be setup by an existing Owens code contributor. +These steps require a secure download, such as through the SSH keys detailed above, to avoid man-in-the-middle attacks. ```julia using Pkg @@ -326,7 +336,7 @@ Pkg.add("PyPlot") #Note, this will take a while (maybe 10 min depending on your # Testing Your Build of OWENS -clone the owens repository which contains example run scripts, the turbine mesh generator +clone the owens repository which contains example scripts that will setup and run example turbines from end to end git clone git@github.com:sandialabs/OWENS.jl @@ -335,13 +345,13 @@ If you get an error about attempting to access library xyz, but it doesn't exist adi_lib = "path/to/openfast/build/modules/libraryfolder/libraryname" ``` - cd OWENS.jl/examples/SNL34m - julia SNL34mVAWTNormalOperation.jl + cd OWENS.jl/examples/literate/ + julia B_detailedInputs.jl You can visualize the output vtk/vtu/pvd paraview files with paraview, install paraview via - apt-get -y install paraview + apt-get -y install paraview # or on mac, brew install paraview -You can also run julia more interactively and maintain variables in scope for inspections etc if you don't have an ide set up (but be careful of assuming a variable was cleared when it wasn't!) by starting the repl and essentially copying and pasing the run script via +You can also run julia more interactively and maintain variables in scope for inspections etc if you don't have an IDE set up (but be careful of assuming a variable was cleared when it wasn't!) by starting the repl and essentially copying and pasing the run script via julia @@ -351,7 +361,7 @@ You can also run julia more interactively and maintain variables in scope for in # Visual Studio Code IDE -You can install VScode and get a debugger etc. In VScode, there is a setting file which sets up VS code for julia and sets some quick keys that can be changed if desired (OWENS.jl/docs/setup/OWENS_Julia_VS.code-profile). +You can install VScode and get a debugger etc. In VScode, there is a setting file which sets up VS code for julia and sets some quick keys that can be changed if desired (OWENS.jl/docs/OWENS.code-profile). With the sample profile loaded into VSCode, If you want to clear out all the variables and restart do diff --git a/docs/src/literate/airfoils/Airfoils.txt b/docs/src/literate/airfoils/Airfoils.txt deleted file mode 100644 index 516c3ad3..00000000 --- a/docs/src/literate/airfoils/Airfoils.txt +++ /dev/null @@ -1,39 +0,0 @@ -04/10/97 - -Coordinates for the SNL airfoils: - - SNL 0015/47 SNL 0018/50 SNL 0021/50 - X (Y X (Y X (Y -0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00020 0.00166 0.00337 0.00646 0.00343 0.00790 -0.00508 0.01091 0.01274 0.01431 0.01291 0.01728 -0.01507 0.02060 0.02713 0.02282 0.02740 0.02735 -0.02872 0.02867 0.04621 0.03160 0.04653 0.03771 -0.04729 0.03615 0.06970 0.04042 0.07001 0.04806 -0.07062 0.04329 0.09730 0.04903 0.09753 0.05814 -0.09832 0.05006 0.12870 0.05726 0.12878 0.06772 -0.13002 0.05630 0.16353 0.06491 0.16339 0.07660 -0.16533 0.06192 0.20142 0.07183 0.20098 0.08460 -0.20386 0.06678 0.24193 0.07786 0.24113 0.09152 -0.24517 0.07080 0.28464 0.08283 0.28339 0.09721 -0.28880 0.07383 0.32907 0.08663 0.32730 0.10149 -0.33426 0.07575 0.37471 0.08908 0.37235 0.10417 -0.38104 0.07643 0.42107 0.09000 0.41805 0.10507 -0.42860 0.07556 0.46759 0.08902 0.46384 0.10379 -0.47688 0.07272 0.51422 0.08561 0.50965 0.09968 -0.52610 0.06808 0.56140 0.07982 0.55603 0.09272 -0.57603 0.06216 0.60914 0.07234 0.60311 0.08368 -0.62618 0.05535 0.65698 0.06379 0.65048 0.07323 -0.67600 0.04801 0.70440 0.05462 0.69767 0.06193 -0.72489 0.04046 0.75083 0.04535 0.74412 0.05037 -0.77244 0.03306 0.79560 0.03642 0.78921 0.03911 -0.81734 0.02608 0.83798 0.02827 0.83220 0.02869 -0.85951 0.01979 0.87718 0.02125 0.87224 0.01959 -0.89801 0.01441 0.91233 0.01562 0.90843 0.01217 -0.93212 0.01005 0.94258 0.01150 0.93980 0.00663 -0.96114 0.00676 0.96711 0.00881 0.96541 0.00296 -0.98447 0.00448 0.98519 0.00740 0.98439 0.00095 -0.99685 0.00349 0.99627 0.00687 0.99606 0.00015 -1.00000 0.00000 1.00000 0.00678 1.00000 0.00000 - -The 18/50 was thickened up near the trailing edge so we could actually build it (we can't make a razor-edged extrusion). Although we had to do a similar thing with the other two airfoils when we built models, I don't have those coordinates available. diff --git a/docs/src/literate/airfoils/NACA_0015.dat b/docs/src/literate/airfoils/NACA_0015.dat deleted file mode 100644 index d2fca4f5..00000000 --- a/docs/src/literate/airfoils/NACA_0015.dat +++ /dev/null @@ -1,1379 +0,0 @@ -Title: NACA0015 -Thickness to Chord Ratio: 0.15 -Zero Lift AOA (deg): 0.0 -Reverse Camber Direction: 0 - -Reynolds Number: 1e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8174 0.4600 0.0000 --26.0000 -0.7639 0.4320 0.0000 --25.0000 -0.7099 0.4050 0.0000 --24.0000 -0.6559 0.3790 0.0000 --23.0000 -0.6019 0.3540 0.0000 --22.0000 -0.5479 0.3290 0.0000 --21.0000 -0.4939 0.3050 0.0000 --20.0000 -0.4399 0.2820 0.0000 --19.0000 -0.3859 0.2600 0.0000 --18.0000 -0.3319 0.2380 0.0000 --17.0000 -0.2780 0.2170 0.0000 --16.0000 -0.2242 0.1960 0.0000 --15.0000 -0.1706 0.1770 0.0000 --14.0000 -0.1172 0.1580 0.0000 --13.0000 -0.0649 0.1400 0.0000 --12.0000 -0.0138 0.1230 0.0000 --11.0000 0.0348 0.1070 0.0000 --10.0000 0.0791 0.0910 0.0000 --9.0000 0.1194 0.0770 0.0000 --8.0000 0.1484 0.0640 0.0000 --7.0000 0.1517 0.0510 0.0000 --6.0000 0.0781 0.0400 0.0000 --5.0000 -0.0162 0.0393 0.0000 --4.0000 -0.0581 0.0383 0.0000 --3.0000 -0.0725 0.0373 0.0000 --2.0000 -0.0715 0.0366 0.0000 --1.0000 -0.0434 0.0362 0.0000 -0.0000 0.0000 0.0360 0.0000 -1.0000 0.0434 0.0362 0.0000 -2.0000 0.0715 0.0366 0.0000 -3.0000 0.0725 0.0373 0.0000 -4.0000 0.0581 0.0383 0.0000 -5.0000 0.0162 0.0393 0.0000 -6.0000 -0.0781 0.0400 0.0000 -7.0000 -0.1517 0.0510 0.0000 -8.0000 -0.1484 0.0640 0.0000 -9.0000 -0.1194 0.0770 0.0000 -10.0000 -0.0791 0.0910 0.0000 -11.0000 -0.0348 0.1070 0.0000 -12.0000 0.0138 0.1230 0.0000 -13.0000 0.0649 0.1400 0.0000 -14.0000 0.1172 0.1580 0.0000 -15.0000 0.1706 0.1770 0.0000 -16.0000 0.2242 0.1960 0.0000 -17.0000 0.2780 0.2170 0.0000 -18.0000 0.3319 0.2380 0.0000 -19.0000 0.3859 0.2600 0.0000 -20.0000 0.4399 0.2820 0.0000 -21.0000 0.4939 0.3050 0.0000 -22.0000 0.5479 0.3290 0.0000 -23.0000 0.6019 0.3540 0.0000 -24.0000 0.6559 0.3790 0.0000 -25.0000 0.7099 0.4050 0.0000 -26.0000 0.7639 0.4320 0.0000 -27.0000 0.8174 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 2e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 2.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -2.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8191 0.4600 0.0000 --26.0000 -0.7649 0.4320 0.0000 --25.0000 -0.7109 0.4050 0.0000 --24.0000 -0.6569 0.3790 0.0000 --23.0000 -0.6029 0.3540 0.0000 --22.0000 -0.5489 0.3290 0.0000 --21.0000 -0.4949 0.3050 0.0000 --20.0000 -0.4409 0.2820 0.0000 --19.0000 -0.3869 0.2600 0.0000 --18.0000 -0.3331 0.2380 0.0000 --17.0000 -0.2792 0.2170 0.0000 --16.0000 -0.2256 0.1960 0.0000 --15.0000 -0.1721 0.1770 0.0000 --14.0000 -0.1193 0.1580 0.0000 --13.0000 -0.0678 0.1400 0.0000 --12.0000 -0.0173 0.1230 0.0000 --11.0000 0.0300 0.1070 0.0000 --10.0000 0.0728 0.0910 0.0000 --9.0000 0.1050 0.0770 0.0000 --8.0000 0.1104 0.0640 0.0000 --7.0000 -0.0570 0.0510 0.0000 --6.0000 -0.3001 0.0410 0.0000 --5.0000 -0.3359 0.0303 0.0000 --4.0000 -0.3041 0.0290 0.0000 --3.0000 -0.2452 0.0279 0.0000 --2.0000 -0.1740 0.0271 0.0000 --1.0000 -0.0891 0.0267 0.0000 -0.0000 0.0000 0.0265 0.0000 -1.0000 0.0891 0.0267 0.0000 -2.0000 0.1740 0.0271 0.0000 -3.0000 0.2452 0.0279 0.0000 -4.0000 0.3041 0.0290 0.0000 -5.0000 0.3359 0.0303 0.0000 -6.0000 0.3001 0.0410 0.0000 -7.0000 0.0570 0.0510 0.0000 -8.0000 -0.1104 0.0640 0.0000 -9.0000 -0.1050 0.0770 0.0000 -10.0000 -0.0728 0.0910 0.0000 -11.0000 -0.0300 0.1070 0.0000 -12.0000 0.0173 0.1230 0.0000 -13.0000 0.0678 0.1400 0.0000 -14.0000 0.1193 0.1580 0.0000 -15.0000 0.1721 0.1770 0.0000 -16.0000 0.2256 0.1960 0.0000 -17.0000 0.2792 0.2170 0.0000 -18.0000 0.3331 0.2380 0.0000 -19.0000 0.3869 0.2600 0.0000 -20.0000 0.4409 0.2820 0.0000 -21.0000 0.4949 0.3050 0.0000 -22.0000 0.5489 0.3290 0.0000 -23.0000 0.6029 0.3540 0.0000 -24.0000 0.6569 0.3790 0.0000 -25.0000 0.7109 0.4050 0.0000 -26.0000 0.7649 0.4320 0.0000 -27.0000 0.8191 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 4e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.879 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.72 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.72 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8222 0.4600 0.0000 --26.0000 -0.7666 0.4320 0.0000 --25.0000 -0.7125 0.4050 0.0000 --24.0000 -0.6585 0.3790 0.0000 --23.0000 -0.6045 0.3540 0.0000 --22.0000 -0.5506 0.3290 0.0000 --21.0000 -0.4966 0.3050 0.0000 --20.0000 -0.4427 0.2820 0.0000 --19.0000 -0.3889 0.2600 0.0000 --18.0000 -0.3351 0.2380 0.0000 --17.0000 -0.2815 0.2170 0.0000 --16.0000 -0.2280 0.1960 0.0000 --15.0000 -0.1756 0.1770 0.0000 --14.0000 -0.1244 0.1580 0.0000 --13.0000 -0.0741 0.1400 0.0000 --12.0000 -0.0261 0.1230 0.0000 --11.0000 0.0144 0.1070 0.0000 --10.0000 0.0413 0.0910 0.0000 --9.0000 -0.0433 0.0770 0.0000 --8.0000 -0.4663 0.0520 0.0000 --7.0000 -0.5730 0.0267 0.0000 --6.0000 -0.5551 0.0249 0.0000 --5.0000 -0.4871 0.0232 0.0000 --4.0000 -0.4017 0.0219 0.0000 --3.0000 -0.3078 0.0209 0.0000 --2.0000 -0.2099 0.0202 0.0000 --1.0000 -0.1054 0.0198 0.0000 -0.0000 0.0000 0.0196 0.0000 -1.0000 0.1054 0.0198 0.0000 -2.0000 0.2099 0.0202 0.0000 -3.0000 0.3078 0.0209 0.0000 -4.0000 0.4017 0.0219 0.0000 -5.0000 0.4871 0.0232 0.0000 -6.0000 0.5551 0.0249 0.0000 -7.0000 0.5730 0.0267 0.0000 -8.0000 0.4663 0.0520 0.0000 -9.0000 0.0433 0.0770 0.0000 -10.0000 -0.0413 0.0910 0.0000 -11.0000 -0.0144 0.1070 0.0000 -12.0000 0.0261 0.1230 0.0000 -13.0000 0.0741 0.1400 0.0000 -14.0000 0.1244 0.1580 0.0000 -15.0000 0.1756 0.1770 0.0000 -16.0000 0.2280 0.1960 0.0000 -17.0000 0.2815 0.2170 0.0000 -18.0000 0.3351 0.2380 0.0000 -19.0000 0.3889 0.2600 0.0000 -20.0000 0.4427 0.2820 0.0000 -21.0000 0.4966 0.3050 0.0000 -22.0000 0.5506 0.3290 0.0000 -23.0000 0.6045 0.3540 0.0000 -24.0000 0.6585 0.3790 0.0000 -25.0000 0.7125 0.4050 0.0000 -26.0000 0.7666 0.4320 0.0000 -27.0000 0.8222 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 8e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.88 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.88 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8277 0.4600 0.0000 --26.0000 -0.7700 0.4320 0.0000 --25.0000 -0.7156 0.4050 0.0000 --24.0000 -0.6617 0.3790 0.0000 --23.0000 -0.6078 0.3540 0.0000 --22.0000 -0.5539 0.3290 0.0000 --21.0000 -0.5001 0.3050 0.0000 --20.0000 -0.4463 0.2820 0.0000 --19.0000 -0.3927 0.2600 0.0000 --18.0000 -0.3393 0.2380 0.0000 --17.0000 -0.2873 0.2170 0.0000 --16.0000 -0.2364 0.1960 0.0000 --15.0000 -0.1861 0.1770 0.0000 --14.0000 -0.1382 0.1580 0.0000 --13.0000 -0.0967 0.1400 0.0000 --12.0000 -0.0749 0.1230 0.0000 --11.0000 -0.1642 0.0760 0.0000 --10.0000 -0.5122 0.0277 0.0000 --9.0000 -0.6969 0.0255 0.0000 --8.0000 -0.7189 0.0234 0.0000 --7.0000 -0.6760 0.0214 0.0000 --6.0000 -0.6048 0.0197 0.0000 --5.0000 -0.5180 0.0181 0.0000 --4.0000 -0.4186 0.0168 0.0000 --3.0000 -0.3300 0.0156 0.0000 --2.0000 -0.2200 0.0151 0.0000 --1.0000 -0.1100 0.0148 0.0000 -0.0000 0.0000 0.0147 0.0000 -1.0000 0.1100 0.0148 0.0000 -2.0000 0.2200 0.0151 0.0000 -3.0000 0.3300 0.0156 0.0000 -4.0000 0.4186 0.0168 0.0000 -5.0000 0.5180 0.0181 0.0000 -6.0000 0.6048 0.0197 0.0000 -7.0000 0.6760 0.0214 0.0000 -8.0000 0.7189 0.0234 0.0000 -9.0000 0.6969 0.0255 0.0000 -10.0000 0.5122 0.0277 0.0000 -11.0000 0.1642 0.0760 0.0000 -12.0000 0.0749 0.1230 0.0000 -13.0000 0.0967 0.1400 0.0000 -14.0000 0.1382 0.1580 0.0000 -15.0000 0.1861 0.1770 0.0000 -16.0000 0.2364 0.1960 0.0000 -17.0000 0.2873 0.2170 0.0000 -18.0000 0.3393 0.2380 0.0000 -19.0000 0.3927 0.2600 0.0000 -20.0000 0.4463 0.2820 0.0000 -21.0000 0.5001 0.3050 0.0000 -22.0000 0.5539 0.3290 0.0000 -23.0000 0.6078 0.3540 0.0000 -24.0000 0.6617 0.3790 0.0000 -25.0000 0.7156 0.4050 0.0000 -26.0000 0.7700 0.4320 0.0000 -27.0000 0.8277 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 1.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.99 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.99 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8382 0.4600 0.0000 --26.0000 -0.7771 0.4320 0.0000 --25.0000 -0.7224 0.4050 0.0000 --24.0000 -0.6685 0.3790 0.0000 --23.0000 -0.6148 0.3540 0.0000 --22.0000 -0.5611 0.3290 0.0000 --21.0000 -0.5087 0.3050 0.0000 --20.0000 -0.4575 0.2820 0.0000 --19.0000 -0.4066 0.2600 0.0000 --18.0000 -0.3567 0.2380 0.0000 --17.0000 -0.3098 0.2170 0.0000 --16.0000 -0.2665 0.1970 0.0000 --15.0000 -0.2376 0.1770 0.0000 --14.0000 -0.2371 0.1040 0.0000 --13.0000 -0.3548 0.0302 0.0000 --12.0000 -0.5936 0.0281 0.0000 --11.0000 -0.7623 0.0256 0.0000 --10.0000 -0.8322 0.0233 0.0000 --9.0000 -0.8311 0.0212 0.0000 --8.0000 -0.7851 0.0193 0.0000 --7.0000 -0.7150 0.0176 0.0000 --6.0000 -0.6299 0.0160 0.0000 --5.0000 -0.5500 0.0142 0.0000 --4.0000 -0.4400 0.0132 0.0000 --3.0000 -0.3300 0.0124 0.0000 --2.0000 -0.2200 0.0120 0.0000 --1.0000 -0.1100 0.0117 0.0000 -0.0000 0.0000 0.0116 0.0000 -1.0000 0.1100 0.0117 0.0000 -2.0000 0.2200 0.0120 0.0000 -3.0000 0.3300 0.0124 0.0000 -4.0000 0.4400 0.0132 0.0000 -5.0000 0.5500 0.0142 0.0000 -6.0000 0.6299 0.0160 0.0000 -7.0000 0.7150 0.0176 0.0000 -8.0000 0.7851 0.0193 0.0000 -9.0000 0.8311 0.0212 0.0000 -10.0000 0.8322 0.0233 0.0000 -11.0000 0.7623 0.0256 0.0000 -12.0000 0.5936 0.0281 0.0000 -13.0000 0.3548 0.0302 0.0000 -14.0000 0.2371 0.1040 0.0000 -15.0000 0.2376 0.1770 0.0000 -16.0000 0.2665 0.1970 0.0000 -17.0000 0.3098 0.2170 0.0000 -18.0000 0.3567 0.2380 0.0000 -19.0000 0.4066 0.2600 0.0000 -20.0000 0.4575 0.2820 0.0000 -21.0000 0.5087 0.3050 0.0000 -22.0000 0.5611 0.3290 0.0000 -23.0000 0.6148 0.3540 0.0000 -24.0000 0.6685 0.3790 0.0000 -25.0000 0.7224 0.4050 0.0000 -26.0000 0.7771 0.4320 0.0000 -27.0000 0.8382 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 3.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.21 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.21 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8788 0.4600 0.0000 --26.0000 -0.8055 0.4320 0.0000 --25.0000 -0.7511 0.4050 0.0000 --24.0000 -0.7015 0.3790 0.0000 --23.0000 -0.6528 0.3540 0.0000 --22.0000 -0.6045 0.3290 0.0000 --21.0000 -0.5616 0.3050 0.0000 --20.0000 -0.5247 0.2820 0.0000 --19.0000 -0.4908 0.2600 0.0000 --18.0000 -0.4782 0.2380 0.0000 --17.0000 -0.4851 0.2170 0.0000 --16.0000 -0.5384 0.1240 0.0000 --15.0000 -0.6350 0.0312 0.0000 --14.0000 -0.7483 0.0283 0.0000 --13.0000 -0.8562 0.0257 0.0000 --12.0000 -0.9285 0.0233 0.0000 --11.0000 -0.9572 0.0211 0.0000 --10.0000 -0.9440 0.0191 0.0000 --9.0000 -0.8946 0.0173 0.0000 --8.0000 -0.8240 0.0157 0.0000 --7.0000 -0.7390 0.0143 0.0000 --6.0000 -0.6600 0.0126 0.0000 --5.0000 -0.5500 0.0114 0.0000 --4.0000 -0.4400 0.0105 0.0000 --3.0000 -0.3300 0.0098 0.0000 --2.0000 -0.2200 0.0094 0.0000 --1.0000 -0.1100 0.0092 0.0000 -0.0000 0.0000 0.0091 0.0000 -1.0000 0.1100 0.0092 0.0000 -2.0000 0.2200 0.0094 0.0000 -3.0000 0.3300 0.0098 0.0000 -4.0000 0.4400 0.0105 0.0000 -5.0000 0.5500 0.0114 0.0000 -6.0000 0.6600 0.0126 0.0000 -7.0000 0.7390 0.0143 0.0000 -8.0000 0.8240 0.0157 0.0000 -9.0000 0.8946 0.0173 0.0000 -10.0000 0.9440 0.0191 0.0000 -11.0000 0.9572 0.0211 0.0000 -12.0000 0.9285 0.0233 0.0000 -13.0000 0.8562 0.0257 0.0000 -14.0000 0.7483 0.0283 0.0000 -15.0000 0.6350 0.0312 0.0000 -16.0000 0.5384 0.1240 0.0000 -17.0000 0.4851 0.2170 0.0000 -18.0000 0.4782 0.2380 0.0000 -19.0000 0.4908 0.2600 0.0000 -20.0000 0.5247 0.2820 0.0000 -21.0000 0.5616 0.3050 0.0000 -22.0000 0.6045 0.3290 0.0000 -23.0000 0.6528 0.3540 0.0000 -24.0000 0.7015 0.3790 0.0000 -25.0000 0.7511 0.4050 0.0000 -26.0000 0.8055 0.4320 0.0000 -27.0000 0.8788 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 7e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.9473 0.4600 0.0000 --26.0000 -0.8838 0.4320 0.0000 --25.0000 -0.8353 0.4050 0.0000 --24.0000 -0.7961 0.3790 0.0000 --23.0000 -0.7593 0.3540 0.0000 --22.0000 -0.7298 0.3290 0.0000 --21.0000 -0.7097 0.3050 0.0000 --20.0000 -0.6990 0.2820 0.0000 --19.0000 -0.7041 0.2600 0.0000 --18.0000 -0.7305 0.2380 0.0000 --17.0000 -0.7799 0.1340 0.0000 --16.0000 -0.8401 0.0297 0.0000 --15.0000 -0.9119 0.0269 0.0000 --14.0000 -0.9801 0.0244 0.0000 --13.0000 -1.0302 0.0221 0.0000 --12.0000 -1.0508 0.0200 0.0000 --11.0000 -1.0363 0.0182 0.0000 --10.0000 -0.9937 0.0164 0.0000 --9.0000 -0.9260 0.0149 0.0000 --8.0000 -0.8442 0.0135 0.0000 --7.0000 -0.7483 0.0122 0.0000 --6.0000 -0.6600 0.0108 0.0000 --5.0000 -0.5500 0.0098 0.0000 --4.0000 -0.4400 0.0089 0.0000 --3.0000 -0.3300 0.0083 0.0000 --2.0000 -0.2200 0.0080 0.0000 --1.0000 -0.1100 0.0078 0.0000 -0.0000 0.0000 0.0077 0.0000 -1.0000 0.1100 0.0078 0.0000 -2.0000 0.2200 0.0080 0.0000 -3.0000 0.3300 0.0083 0.0000 -4.0000 0.4400 0.0089 0.0000 -5.0000 0.5500 0.0098 0.0000 -6.0000 0.6600 0.0108 0.0000 -7.0000 0.7483 0.0122 0.0000 -8.0000 0.8442 0.0135 0.0000 -9.0000 0.9260 0.0149 0.0000 -10.0000 0.9937 0.0164 0.0000 -11.0000 1.0363 0.0182 0.0000 -12.0000 1.0508 0.0200 0.0000 -13.0000 1.0302 0.0221 0.0000 -14.0000 0.9801 0.0244 0.0000 -15.0000 0.9119 0.0269 0.0000 -16.0000 0.8401 0.0297 0.0000 -17.0000 0.7799 0.1340 0.0000 -18.0000 0.7305 0.2380 0.0000 -19.0000 0.7041 0.2600 0.0000 -20.0000 0.6990 0.2820 0.0000 -21.0000 0.7097 0.3050 0.0000 -22.0000 0.7298 0.3290 0.0000 -23.0000 0.7593 0.3540 0.0000 -24.0000 0.7961 0.3790 0.0000 -25.0000 0.8353 0.4050 0.0000 -26.0000 0.8838 0.4320 0.0000 -27.0000 0.9473 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 1e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 7.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -7.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.9912 0.4600 0.0000 --26.0000 -0.9406 0.4320 0.0000 --25.0000 -0.9023 0.4050 0.0000 --24.0000 -0.8668 0.3790 0.0000 --23.0000 -0.8408 0.3540 0.0000 --22.0000 -0.8189 0.3290 0.0000 --21.0000 -0.8063 0.3050 0.0000 --20.0000 -0.8089 0.2820 0.0000 --19.0000 -0.8226 0.2600 0.0000 --18.0000 -0.8566 0.1450 0.0000 --17.0000 -0.8996 0.0303 0.0000 --16.0000 -0.9567 0.0275 0.0000 --15.0000 -1.0145 0.0249 0.0000 --14.0000 -1.0656 0.0225 0.0000 --13.0000 -1.0957 0.0205 0.0000 --12.0000 -1.0971 0.0186 0.0000 --11.0000 -1.0686 0.0168 0.0000 --10.0000 -1.0141 0.0152 0.0000 --9.0000 -0.9387 0.0138 0.0000 --8.0000 -0.8504 0.0126 0.0000 --7.0000 -0.7700 0.0111 0.0000 --6.0000 -0.6600 0.0101 0.0000 --5.0000 -0.5500 0.0091 0.0000 --4.0000 -0.4400 0.0083 0.0000 --3.0000 -0.3300 0.0079 0.0000 --2.0000 -0.2200 0.0076 0.0000 --1.0000 -0.1100 0.0075 0.0000 -0.0000 0.0000 0.0074 0.0000 -1.0000 0.1100 0.0075 0.0000 -2.0000 0.2200 0.0076 0.0000 -3.0000 0.3300 0.0079 0.0000 -4.0000 0.4400 0.0083 0.0000 -5.0000 0.5500 0.0091 0.0000 -6.0000 0.6600 0.0101 0.0000 -7.0000 0.7700 0.0111 0.0000 -8.0000 0.8504 0.0126 0.0000 -9.0000 0.9387 0.0138 0.0000 -10.0000 1.0141 0.0152 0.0000 -11.0000 1.0686 0.0168 0.0000 -12.0000 1.0971 0.0186 0.0000 -13.0000 1.0957 0.0205 0.0000 -14.0000 1.0656 0.0225 0.0000 -15.0000 1.0145 0.0249 0.0000 -16.0000 0.9567 0.0275 0.0000 -17.0000 0.8996 0.0303 0.0000 -18.0000 0.8566 0.1450 0.0000 -19.0000 0.8226 0.2600 0.0000 -20.0000 0.8089 0.2820 0.0000 -21.0000 0.8063 0.3050 0.0000 -22.0000 0.8189 0.3290 0.0000 -23.0000 0.8408 0.3540 0.0000 -24.0000 0.8668 0.3790 0.0000 -25.0000 0.9023 0.4050 0.0000 -26.0000 0.9406 0.4320 0.0000 -27.0000 0.9912 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 2e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 8.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -8.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.43 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.43 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -1.0810 0.4600 0.0000 --26.0000 -1.0591 0.4320 0.0000 --25.0000 -1.0317 0.4050 0.0000 --24.0000 -1.0078 0.3790 0.0000 --23.0000 -0.9910 0.3540 0.0000 --22.0000 -0.9827 0.3290 0.0000 --21.0000 -0.9837 0.3050 0.0000 --20.0000 -0.9954 0.2820 0.0000 --19.0000 -1.0173 0.1550 0.0000 --18.0000 -1.0510 0.0288 0.0000 --17.0000 -1.0921 0.0261 0.0000 --16.0000 -1.1356 0.0237 0.0000 --15.0000 -1.1744 0.0215 0.0000 --14.0000 -1.1962 0.0195 0.0000 --13.0000 -1.1948 0.0177 0.0000 --12.0000 -1.1667 0.0161 0.0000 --11.0000 -1.1138 0.0146 0.0000 --10.0000 -1.0433 0.0133 0.0000 --9.0000 -0.9574 0.0121 0.0000 --8.0000 -0.8800 0.0108 0.0000 --7.0000 -0.7700 0.0098 0.0000 --6.0000 -0.6600 0.0090 0.0000 --5.0000 -0.5500 0.0083 0.0000 --4.0000 -0.4400 0.0078 0.0000 --3.0000 -0.3300 0.0075 0.0000 --2.0000 -0.2200 0.0072 0.0000 --1.0000 -0.1100 0.0071 0.0000 -0.0000 0.0000 0.0070 0.0000 -1.0000 0.1100 0.0071 0.0000 -2.0000 0.2200 0.0072 0.0000 -3.0000 0.3300 0.0075 0.0000 -4.0000 0.4400 0.0078 0.0000 -5.0000 0.5500 0.0083 0.0000 -6.0000 0.6600 0.0090 0.0000 -7.0000 0.7700 0.0098 0.0000 -8.0000 0.8800 0.0108 0.0000 -9.0000 0.9574 0.0121 0.0000 -10.0000 1.0433 0.0133 0.0000 -11.0000 1.1138 0.0146 0.0000 -12.0000 1.1667 0.0161 0.0000 -13.0000 1.1948 0.0177 0.0000 -14.0000 1.1962 0.0195 0.0000 -15.0000 1.1744 0.0215 0.0000 -16.0000 1.1356 0.0237 0.0000 -17.0000 1.0921 0.0261 0.0000 -18.0000 1.0510 0.0288 0.0000 -19.0000 1.0173 0.1550 0.0000 -20.0000 0.9954 0.2820 0.0000 -21.0000 0.9837 0.3050 0.0000 -22.0000 0.9827 0.3290 0.0000 -23.0000 0.9910 0.3540 0.0000 -24.0000 1.0078 0.3790 0.0000 -25.0000 1.0317 0.4050 0.0000 -26.0000 1.0591 0.4320 0.0000 -27.0000 1.0810 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 5e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 9.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -9.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -1.1397 0.4600 0.0000 --26.0000 -1.1268 0.4320 0.0000 --25.0000 -1.1322 0.4050 0.0000 --24.0000 -1.1563 0.3790 0.0000 --23.0000 -1.1611 0.3540 0.0000 --22.0000 -1.1647 0.3290 0.0000 --21.0000 -1.1771 0.3050 0.0000 --20.0000 -1.1965 0.1660 0.0000 --19.0000 -1.2242 0.0265 0.0000 --18.0000 -1.2576 0.0240 0.0000 --17.0000 -1.2917 0.0218 0.0000 --16.0000 -1.3186 0.0198 0.0000 --15.0000 -1.3298 0.0180 0.0000 --14.0000 -1.3187 0.0164 0.0000 --13.0000 -1.2847 0.0149 0.0000 --12.0000 -1.2290 0.0136 0.0000 --11.0000 -1.1553 0.0124 0.0000 --10.0000 -1.0685 0.0113 0.0000 --9.0000 -0.9900 0.0102 0.0000 --8.0000 -0.8800 0.0095 0.0000 --7.0000 -0.7700 0.0089 0.0000 --6.0000 -0.6600 0.0084 0.0000 --5.0000 -0.5500 0.0080 0.0000 --4.0000 -0.4400 0.0075 0.0000 --3.0000 -0.3300 0.0073 0.0000 --2.0000 -0.2200 0.0070 0.0000 --1.0000 -0.1100 0.0069 0.0000 -0.0000 0.0000 0.0068 0.0000 -1.0000 0.1100 0.0069 0.0000 -2.0000 0.2200 0.0070 0.0000 -3.0000 0.3300 0.0073 0.0000 -4.0000 0.4400 0.0075 0.0000 -5.0000 0.5500 0.0080 0.0000 -6.0000 0.6600 0.0084 0.0000 -7.0000 0.7700 0.0089 0.0000 -8.0000 0.8800 0.0095 0.0000 -9.0000 0.9900 0.0102 0.0000 -10.0000 1.0685 0.0113 0.0000 -11.0000 1.1553 0.0124 0.0000 -12.0000 1.2290 0.0136 0.0000 -13.0000 1.2847 0.0149 0.0000 -14.0000 1.3187 0.0164 0.0000 -15.0000 1.3298 0.0180 0.0000 -16.0000 1.3186 0.0198 0.0000 -17.0000 1.2917 0.0218 0.0000 -18.0000 1.2576 0.0240 0.0000 -19.0000 1.2242 0.0265 0.0000 -20.0000 1.1965 0.1660 0.0000 -21.0000 1.1771 0.3050 0.0000 -22.0000 1.1647 0.3290 0.0000 -23.0000 1.1611 0.3540 0.0000 -24.0000 1.1563 0.3790 0.0000 -25.0000 1.1322 0.4050 0.0000 -26.0000 1.1268 0.4320 0.0000 -27.0000 1.1397 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 - -Reynolds Number: 1e7 -BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -1.1519 0.4600 0.0000 --26.0000 -1.1374 0.4320 0.0000 --25.0000 -1.1380 0.4050 0.0000 --24.0000 -1.1538 0.3790 0.0000 --23.0000 -1.1981 0.3540 0.0000 --22.0000 -1.2767 0.3290 0.0000 --21.0000 -1.3077 0.1770 0.0000 --20.0000 -1.3325 0.0257 0.0000 --19.0000 -1.3608 0.0234 0.0000 --18.0000 -1.3897 0.0213 0.0000 --17.0000 -1.4136 0.0194 0.0000 --16.0000 -1.4233 0.0176 0.0000 --15.0000 -1.4136 0.0161 0.0000 --14.0000 -1.3825 0.0147 0.0000 --13.0000 -1.3300 0.0134 0.0000 --12.0000 -1.2591 0.0123 0.0000 --11.0000 -1.1749 0.0114 0.0000 --10.0000 -1.1000 0.0103 0.0000 --9.0000 -0.9900 0.0096 0.0000 --8.0000 -0.8800 0.0090 0.0000 --7.0000 -0.7700 0.0086 0.0000 --6.0000 -0.6600 0.0081 0.0000 --5.0000 -0.5500 0.0077 0.0000 --4.0000 -0.4400 0.0074 0.0000 --3.0000 -0.3300 0.0071 0.0000 --2.0000 -0.2200 0.0069 0.0000 --1.0000 -0.1100 0.0068 0.0000 -0.0000 0.0000 0.0068 0.0000 -1.0000 0.1100 0.0068 0.0000 -2.0000 0.2200 0.0069 0.0000 -3.0000 0.3300 0.0071 0.0000 -4.0000 0.4400 0.0074 0.0000 -5.0000 0.5500 0.0077 0.0000 -6.0000 0.6600 0.0081 0.0000 -7.0000 0.7700 0.0086 0.0000 -8.0000 0.8800 0.0090 0.0000 -9.0000 0.9900 0.0096 0.0000 -10.0000 1.1000 0.0103 0.0000 -11.0000 1.1749 0.0114 0.0000 -12.0000 1.2591 0.0123 0.0000 -13.0000 1.3300 0.0134 0.0000 -14.0000 1.3825 0.0147 0.0000 -15.0000 1.4136 0.0161 0.0000 -16.0000 1.4233 0.0176 0.0000 -17.0000 1.4136 0.0194 0.0000 -18.0000 1.3897 0.0213 0.0000 -19.0000 1.3608 0.0234 0.0000 -20.0000 1.3325 0.0257 0.0000 -21.0000 1.3077 0.1770 0.0000 -22.0000 1.2767 0.3290 0.0000 -23.0000 1.1981 0.3540 0.0000 -24.0000 1.1538 0.3790 0.0000 -25.0000 1.1380 0.4050 0.0000 -26.0000 1.1374 0.4320 0.0000 -27.0000 1.1519 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 diff --git a/docs/src/literate/airfoils/NACA_0015_RE3E5.dat b/docs/src/literate/airfoils/NACA_0015_RE3E5.dat deleted file mode 100644 index 9056804e..00000000 --- a/docs/src/literate/airfoils/NACA_0015_RE3E5.dat +++ /dev/null @@ -1,130 +0,0 @@ -Title: NACA0015 -Thickness to Chord Ratio: 0.15 -Zero Lift AOA (deg): 0.0 -Reverse Camber Direction: 0 -Reynolds Number: 3.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.21 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.21 -skipline -AOA (deg) CL CD Cm25 --180.0000 0.0000 0.0250 0.0000 --175.0000 0.6600 0.0550 0.0000 --170.0000 0.8500 0.1400 0.0000 --165.0000 0.6800 0.2300 0.0000 --160.0000 0.6350 0.3200 0.0000 --155.0000 0.6700 0.4200 0.0000 --150.0000 0.7700 0.5750 0.0000 --145.0000 0.9000 0.7550 0.0000 --140.0000 0.9800 0.9250 0.0000 --135.0000 0.9300 1.0850 0.0000 --130.0000 0.8500 1.2250 0.0000 --125.0000 0.7600 1.3500 0.0000 --120.0000 0.6700 1.4650 0.0000 --115.0000 0.5750 1.5550 0.0000 --110.0000 0.4500 1.6350 0.0000 --105.0000 0.3200 1.7000 0.0000 --100.0000 0.1850 1.7500 0.0000 --95.0000 0.0500 1.7800 0.0000 --90.0000 -0.0900 1.8000 0.0000 --85.0000 -0.2300 1.8000 0.0000 --80.0000 -0.3650 1.7800 0.0000 --75.0000 -0.5000 1.7350 0.0000 --70.0000 -0.6300 1.6650 0.0000 --65.0000 -0.7600 1.5750 0.0000 --60.0000 -0.8750 1.4700 0.0000 --55.0000 -0.9550 1.3450 0.0000 --50.0000 -1.0200 1.2150 0.0000 --45.0000 -1.0500 1.0750 0.0000 --40.0000 -1.0350 0.9200 0.0000 --35.0000 -0.9800 0.7450 0.0000 --30.0000 -0.8550 0.5700 0.0000 --27.0000 -0.8788 0.4600 0.0000 --26.0000 -0.8055 0.4320 0.0000 --25.0000 -0.7511 0.4050 0.0000 --24.0000 -0.7015 0.3790 0.0000 --23.0000 -0.6528 0.3540 0.0000 --22.0000 -0.6045 0.3290 0.0000 --21.0000 -0.5616 0.3050 0.0000 --20.0000 -0.5247 0.2820 0.0000 --19.0000 -0.4908 0.2600 0.0000 --18.0000 -0.4782 0.2380 0.0000 --17.0000 -0.4851 0.2170 0.0000 --16.0000 -0.5384 0.1240 0.0000 --15.0000 -0.6350 0.0312 0.0000 --14.0000 -0.7483 0.0283 0.0000 --13.0000 -0.8562 0.0257 0.0000 --12.0000 -0.9285 0.0233 0.0000 --11.0000 -0.9572 0.0211 0.0000 --10.0000 -0.9440 0.0191 0.0000 --9.0000 -0.8946 0.0173 0.0000 --8.0000 -0.8240 0.0157 0.0000 --7.0000 -0.7390 0.0143 0.0000 --6.0000 -0.6600 0.0126 0.0000 --5.0000 -0.5500 0.0114 0.0000 --4.0000 -0.4400 0.0105 0.0000 --3.0000 -0.3300 0.0098 0.0000 --2.0000 -0.2200 0.0094 0.0000 --1.0000 -0.1100 0.0092 0.0000 -0.0000 0.0000 0.0091 0.0000 -1.0000 0.1100 0.0092 0.0000 -2.0000 0.2200 0.0094 0.0000 -3.0000 0.3300 0.0098 0.0000 -4.0000 0.4400 0.0105 0.0000 -5.0000 0.5500 0.0114 0.0000 -6.0000 0.6600 0.0126 0.0000 -7.0000 0.7390 0.0143 0.0000 -8.0000 0.8240 0.0157 0.0000 -9.0000 0.8946 0.0173 0.0000 -10.0000 0.9440 0.0191 0.0000 -11.0000 0.9572 0.0211 0.0000 -12.0000 0.9285 0.0233 0.0000 -13.0000 0.8562 0.0257 0.0000 -14.0000 0.7483 0.0283 0.0000 -15.0000 0.6350 0.0312 0.0000 -16.0000 0.5384 0.1240 0.0000 -17.0000 0.4851 0.2170 0.0000 -18.0000 0.4782 0.2380 0.0000 -19.0000 0.4908 0.2600 0.0000 -20.0000 0.5247 0.2820 0.0000 -21.0000 0.5616 0.3050 0.0000 -22.0000 0.6045 0.3290 0.0000 -23.0000 0.6528 0.3540 0.0000 -24.0000 0.7015 0.3790 0.0000 -25.0000 0.7511 0.4050 0.0000 -26.0000 0.8055 0.4320 0.0000 -27.0000 0.8788 0.4600 0.0000 -30.0000 0.8550 0.5700 0.0000 -35.0000 0.9800 0.7450 0.0000 -40.0000 1.0350 0.9200 0.0000 -45.0000 1.0500 1.0750 0.0000 -50.0000 1.0200 1.2150 0.0000 -55.0000 0.9550 1.3450 0.0000 -60.0000 0.8750 1.4700 0.0000 -65.0000 0.7600 1.5750 0.0000 -70.0000 0.6300 1.6650 0.0000 -75.0000 0.5000 1.7350 0.0000 -80.0000 0.3650 1.7800 0.0000 -85.0000 0.2300 1.8000 0.0000 -90.0000 0.0900 1.8000 0.0000 -95.0000 -0.0500 1.7800 0.0000 -100.0000 -0.1850 1.7500 0.0000 -105.0000 -0.3200 1.7000 0.0000 -110.0000 -0.4500 1.6350 0.0000 -115.0000 -0.5750 1.5550 0.0000 -120.0000 -0.6700 1.4650 0.0000 -125.0000 -0.7600 1.3500 0.0000 -130.0000 -0.8500 1.2250 0.0000 -135.0000 -0.9300 1.0850 0.0000 -140.0000 -0.9800 0.9250 0.0000 -145.0000 -0.9000 0.7550 0.0000 -150.0000 -0.7700 0.5750 0.0000 -155.0000 -0.6700 0.4200 0.0000 -160.0000 -0.6350 0.3200 0.0000 -165.0000 -0.6800 0.2300 0.0000 -170.0000 -0.8500 0.1400 0.0000 -175.0000 -0.6600 0.0550 0.0000 -180.0000 0.0000 0.0250 0.0000 -EOT diff --git a/docs/src/literate/airfoils/NACA_0018_AllRe.dat b/docs/src/literate/airfoils/NACA_0018_AllRe.dat deleted file mode 100644 index e4b94c5a..00000000 --- a/docs/src/literate/airfoils/NACA_0018_AllRe.dat +++ /dev/null @@ -1,1464 +0,0 @@ -! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- -! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million -! line -! line -! ------------------------------------------------------------------------------ -DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] -0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) -1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) -@"NACA_0018_Coords.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. -"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. -10 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. -! ------------------------------------------------------------------------------ -! data for table 1 -! ------------------------------------------------------------------------------ -0.01 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -8.136711569484852 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --8.136711569484852 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -1.8163 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.1482 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.1545 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -99 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -5.77500000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -4.17200000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -3.11100000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -2.07000000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -1.05100000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -8.50000000e-03 1.58000000e-01 0.00000000e+00 --1.20000000e+01 7.67000000e-02 1.23000000e-01 0.00000000e+00 --1.10000000e+01 1.12500000e-01 8.00000000e-02 0.00000000e+00 --1.00000000e+01 1.42300000e-01 5.74000000e-02 0.00000000e+00 --9.00000000e+00 1.58400000e-01 5.25000000e-02 0.00000000e+00 --8.00000000e+00 1.50100000e-01 4.89000000e-02 0.00000000e+00 --7.00000000e+00 1.18200000e-01 4.63000000e-02 0.00000000e+00 --6.00000000e+00 8.39000000e-02 4.43000000e-02 0.00000000e+00 --5.00000000e+00 5.77000000e-02 4.25000000e-02 0.00000000e+00 --4.00000000e+00 3.68000000e-02 4.10000000e-02 0.00000000e+00 --3.00000000e+00 2.33000000e-02 3.99000000e-02 0.00000000e+00 --2.00000000e+00 1.54000000e-02 3.91000000e-02 0.00000000e+00 --1.00000000e+00 4.50000000e-03 3.87000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 3.85000000e-02 0.00000000e+00 - 1.00000000e+00 -4.50000000e-03 3.87000000e-02 0.00000000e+00 - 2.00000000e+00 -1.54000000e-02 3.91000000e-02 0.00000000e+00 - 3.00000000e+00 -2.33000000e-02 3.99000000e-02 0.00000000e+00 - 4.00000000e+00 -3.68000000e-02 4.10000000e-02 0.00000000e+00 - 5.00000000e+00 -5.77000000e-02 4.25000000e-02 0.00000000e+00 - 6.00000000e+00 -8.39000000e-02 4.43000000e-02 0.00000000e+00 - 7.00000000e+00 -1.18200000e-01 4.63000000e-02 0.00000000e+00 - 8.00000000e+00 -1.50100000e-01 4.89000000e-02 0.00000000e+00 - 9.00000000e+00 -1.58400000e-01 5.25000000e-02 0.00000000e+00 - 1.00000000e+01 -1.42300000e-01 5.74000000e-02 0.00000000e+00 - 1.10000000e+01 -1.12500000e-01 8.00000000e-02 0.00000000e+00 - 1.20000000e+01 -7.67000000e-02 1.23000000e-01 0.00000000e+00 - 1.40000000e+01 8.50000000e-03 1.58000000e-01 0.00000000e+00 - 1.60000000e+01 1.05100000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 2.07000000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 3.11100000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 4.17200000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 5.77500000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 2 -! ------------------------------------------------------------------------------ -0.02 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -9.154276388714532 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --9.154276388714532 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.1809 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.1809 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0286 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -97 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -5.79800000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -4.19800000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -3.15100000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -2.12000000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -1.11400000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -1.72000000e-02 1.58000000e-01 0.00000000e+00 --1.20000000e+01 6.02000000e-02 1.23000000e-01 0.00000000e+00 --1.00000000e+01 1.00300000e-01 6.30000000e-02 0.00000000e+00 --9.00000000e+00 6.82000000e-02 3.96000000e-02 0.00000000e+00 --8.00000000e+00 -2.14000000e-02 3.76000000e-02 0.00000000e+00 --7.00000000e+00 -1.16100000e-01 3.58000000e-02 0.00000000e+00 --6.00000000e+00 -1.58200000e-01 3.39000000e-02 0.00000000e+00 --5.00000000e+00 -1.78800000e-01 3.23000000e-02 0.00000000e+00 --4.00000000e+00 -1.78800000e-01 3.10000000e-02 0.00000000e+00 --3.00000000e+00 -1.55000000e-01 2.99000000e-02 0.00000000e+00 --2.00000000e+00 -1.13500000e-01 2.92000000e-02 0.00000000e+00 --1.00000000e+00 -6.07000000e-02 2.88000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 2.86000000e-02 0.00000000e+00 - 1.00000000e+00 6.07000000e-02 2.88000000e-02 0.00000000e+00 - 2.00000000e+00 1.13500000e-01 2.92000000e-02 0.00000000e+00 - 3.00000000e+00 1.55000000e-01 2.99000000e-02 0.00000000e+00 - 4.00000000e+00 1.78800000e-01 3.10000000e-02 0.00000000e+00 - 5.00000000e+00 1.78800000e-01 3.23000000e-02 0.00000000e+00 - 6.00000000e+00 1.58200000e-01 3.39000000e-02 0.00000000e+00 - 7.00000000e+00 1.16100000e-01 3.58000000e-02 0.00000000e+00 - 8.00000000e+00 2.14000000e-02 3.76000000e-02 0.00000000e+00 - 9.00000000e+00 -6.82000000e-02 3.96000000e-02 0.00000000e+00 - 1.00000000e+01 -1.00300000e-01 6.30000000e-02 0.00000000e+00 - 1.20000000e+01 -6.02000000e-02 1.23000000e-01 0.00000000e+00 - 1.40000000e+01 1.72000000e-02 1.58000000e-01 0.00000000e+00 - 1.60000000e+01 1.11400000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 2.12000000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 3.15100000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 4.19800000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 5.79800000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 3 -! ------------------------------------------------------------------------------ -0.04 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -10.299096322309719 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --10.299096322309719 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.4757 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -97 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -5.84000000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -4.26500000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -3.23600000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -2.22800000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -1.28700000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -4.89000000e-02 1.58000000e-01 0.00000000e+00 --1.20000000e+01 -1.39000000e-02 1.23000000e-01 0.00000000e+00 --1.00000000e+01 -2.10800000e-01 6.20000000e-02 0.00000000e+00 --9.00000000e+00 -3.54400000e-01 3.27000000e-02 0.00000000e+00 --8.00000000e+00 -4.42800000e-01 3.03000000e-02 0.00000000e+00 --7.00000000e+00 -4.75800000e-01 2.82000000e-02 0.00000000e+00 --6.00000000e+00 -4.57300000e-01 2.63000000e-02 0.00000000e+00 --5.00000000e+00 -4.11700000e-01 2.47000000e-02 0.00000000e+00 --4.00000000e+00 -3.49500000e-01 2.35000000e-02 0.00000000e+00 --3.00000000e+00 -2.68800000e-01 2.25000000e-02 0.00000000e+00 --2.00000000e+00 -1.83300000e-01 2.19000000e-02 0.00000000e+00 --1.00000000e+00 -9.36000000e-02 2.15000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 2.14000000e-02 0.00000000e+00 - 1.00000000e+00 9.36000000e-02 2.15000000e-02 0.00000000e+00 - 2.00000000e+00 1.83300000e-01 2.19000000e-02 0.00000000e+00 - 3.00000000e+00 2.68800000e-01 2.25000000e-02 0.00000000e+00 - 4.00000000e+00 3.49500000e-01 2.35000000e-02 0.00000000e+00 - 5.00000000e+00 4.11700000e-01 2.47000000e-02 0.00000000e+00 - 6.00000000e+00 4.57300000e-01 2.63000000e-02 0.00000000e+00 - 7.00000000e+00 4.75800000e-01 2.82000000e-02 0.00000000e+00 - 8.00000000e+00 4.42800000e-01 3.03000000e-02 0.00000000e+00 - 9.00000000e+00 3.54400000e-01 3.27000000e-02 0.00000000e+00 - 1.00000000e+01 2.10800000e-01 6.20000000e-02 0.00000000e+00 - 1.20000000e+01 1.39000000e-02 1.23000000e-01 0.00000000e+00 - 1.40000000e+01 4.89000000e-02 1.58000000e-01 0.00000000e+00 - 1.60000000e+01 1.28700000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 2.22800000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 3.23600000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 4.26500000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 5.84000000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 4 -! ------------------------------------------------------------------------------ -0.08 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -11.587085702041861 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --11.587085702041861 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.6566 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -99 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -5.96300000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -4.43000000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -3.47200000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -2.60300000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -2.02700000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -2.25600000e-01 1.58000000e-01 0.00000000e+00 --1.20000000e+01 -4.40800000e-01 8.00000000e-02 0.00000000e+00 --1.10000000e+01 -5.53100000e-01 3.15000000e-02 0.00000000e+00 --1.00000000e+01 -6.24800000e-01 2.88000000e-02 0.00000000e+00 --9.00000000e+00 -6.60600000e-01 2.64000000e-02 0.00000000e+00 --8.00000000e+00 -6.58900000e-01 2.42000000e-02 0.00000000e+00 --7.00000000e+00 -6.22400000e-01 2.23000000e-02 0.00000000e+00 --6.00000000e+00 -5.61500000e-01 2.06000000e-02 0.00000000e+00 --5.00000000e+00 -4.75300000e-01 1.92000000e-02 0.00000000e+00 --4.00000000e+00 -3.88000000e-01 1.81000000e-02 0.00000000e+00 --3.00000000e+00 -2.92400000e-01 1.72000000e-02 0.00000000e+00 --2.00000000e+00 -1.93500000e-01 1.67000000e-02 0.00000000e+00 --1.00000000e+00 -8.89000000e-02 1.63000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 1.62000000e-02 0.00000000e+00 - 1.00000000e+00 8.89000000e-02 1.63000000e-02 0.00000000e+00 - 2.00000000e+00 1.93500000e-01 1.67000000e-02 0.00000000e+00 - 3.00000000e+00 2.92400000e-01 1.72000000e-02 0.00000000e+00 - 4.00000000e+00 3.88000000e-01 1.81000000e-02 0.00000000e+00 - 5.00000000e+00 4.75300000e-01 1.92000000e-02 0.00000000e+00 - 6.00000000e+00 5.61500000e-01 2.06000000e-02 0.00000000e+00 - 7.00000000e+00 6.22400000e-01 2.23000000e-02 0.00000000e+00 - 8.00000000e+00 6.58900000e-01 2.42000000e-02 0.00000000e+00 - 9.00000000e+00 6.60600000e-01 2.64000000e-02 0.00000000e+00 - 1.00000000e+01 6.24800000e-01 2.88000000e-02 0.00000000e+00 - 1.10000000e+01 5.53100000e-01 3.15000000e-02 0.00000000e+00 - 1.20000000e+01 4.40800000e-01 8.00000000e-02 0.00000000e+00 - 1.40000000e+01 2.25600000e-01 1.58000000e-01 0.00000000e+00 - 1.60000000e+01 2.02700000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 2.60300000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 3.47200000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 4.43000000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 5.96300000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 5 -! ------------------------------------------------------------------------------ -0.16 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -13.036149081898586 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --13.036149081898586 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.787 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -101 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -6.32100000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -5.02600000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -4.38200000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -4.20200000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -4.89600000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -6.23700000e-01 1.58000000e-01 0.00000000e+00 --1.30000000e+01 -6.92300000e-01 7.70000000e-02 0.00000000e+00 --1.20000000e+01 -7.48800000e-01 2.88000000e-02 0.00000000e+00 --1.10000000e+01 -7.85200000e-01 2.62000000e-02 0.00000000e+00 --1.00000000e+01 -7.94900000e-01 2.38000000e-02 0.00000000e+00 --9.00000000e+00 -7.78100000e-01 2.17000000e-02 0.00000000e+00 --8.00000000e+00 -7.37300000e-01 1.98000000e-02 0.00000000e+00 --7.00000000e+00 -6.72400000e-01 1.81000000e-02 0.00000000e+00 --6.00000000e+00 -5.96000000e-01 1.66000000e-02 0.00000000e+00 --5.00000000e+00 -5.06800000e-01 1.53000000e-02 0.00000000e+00 --4.00000000e+00 -4.11400000e-01 1.44000000e-02 0.00000000e+00 --3.00000000e+00 -3.08800000e-01 1.37000000e-02 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 1.31000000e-02 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 1.29000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 1.28000000e-02 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 1.29000000e-02 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 1.31000000e-02 0.00000000e+00 - 3.00000000e+00 3.08800000e-01 1.37000000e-02 0.00000000e+00 - 4.00000000e+00 4.11400000e-01 1.44000000e-02 0.00000000e+00 - 5.00000000e+00 5.06800000e-01 1.53000000e-02 0.00000000e+00 - 6.00000000e+00 5.96000000e-01 1.66000000e-02 0.00000000e+00 - 7.00000000e+00 6.72400000e-01 1.81000000e-02 0.00000000e+00 - 8.00000000e+00 7.37300000e-01 1.98000000e-02 0.00000000e+00 - 9.00000000e+00 7.78100000e-01 2.17000000e-02 0.00000000e+00 - 1.00000000e+01 7.94900000e-01 2.38000000e-02 0.00000000e+00 - 1.10000000e+01 7.85200000e-01 2.62000000e-02 0.00000000e+00 - 1.20000000e+01 7.48800000e-01 2.88000000e-02 0.00000000e+00 - 1.30000000e+01 6.92300000e-01 7.70000000e-02 0.00000000e+00 - 1.40000000e+01 6.23700000e-01 1.58000000e-01 0.00000000e+00 - 1.60000000e+01 4.89600000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 4.20200000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 4.38200000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 5.02600000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 6.32100000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 6 -! ------------------------------------------------------------------------------ -0.36 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -14.963057557300898 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --14.963057557300898 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --0.9125 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -101 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -7.72400000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -7.05000000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -6.99700000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -7.31900000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -8.00700000e-01 1.96000000e-01 0.00000000e+00 --1.40000000e+01 -8.80300000e-01 9.40000000e-02 0.00000000e+00 --1.30000000e+01 -9.10400000e-01 2.59000000e-02 0.00000000e+00 --1.20000000e+01 -9.27900000e-01 2.35000000e-02 0.00000000e+00 --1.10000000e+01 -9.24900000e-01 2.13000000e-02 0.00000000e+00 --1.00000000e+01 -8.98300000e-01 1.94000000e-02 0.00000000e+00 --9.00000000e+00 -8.52600000e-01 1.76000000e-02 0.00000000e+00 --8.00000000e+00 -7.87900000e-01 1.59000000e-02 0.00000000e+00 --7.00000000e+00 -7.10000000e-01 1.45000000e-02 0.00000000e+00 --6.00000000e+00 -6.22800000e-01 1.32000000e-02 0.00000000e+00 --5.00000000e+00 -5.24000000e-01 1.21000000e-02 0.00000000e+00 --4.00000000e+00 -4.40000000e-01 1.12000000e-02 0.00000000e+00 --3.00000000e+00 -3.30000000e-01 1.07000000e-02 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 1.04000000e-02 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 1.02000000e-02 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 1.01000000e-02 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 1.02000000e-02 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 1.04000000e-02 0.00000000e+00 - 3.00000000e+00 3.30000000e-01 1.07000000e-02 0.00000000e+00 - 4.00000000e+00 4.40000000e-01 1.12000000e-02 0.00000000e+00 - 5.00000000e+00 5.24000000e-01 1.21000000e-02 0.00000000e+00 - 6.00000000e+00 6.22800000e-01 1.32000000e-02 0.00000000e+00 - 7.00000000e+00 7.10000000e-01 1.45000000e-02 0.00000000e+00 - 8.00000000e+00 7.87900000e-01 1.59000000e-02 0.00000000e+00 - 9.00000000e+00 8.52600000e-01 1.76000000e-02 0.00000000e+00 - 1.00000000e+01 8.98300000e-01 1.94000000e-02 0.00000000e+00 - 1.10000000e+01 9.24900000e-01 2.13000000e-02 0.00000000e+00 - 1.20000000e+01 9.27900000e-01 2.35000000e-02 0.00000000e+00 - 1.30000000e+01 9.10400000e-01 2.59000000e-02 0.00000000e+00 - 1.40000000e+01 8.80300000e-01 9.40000000e-02 0.00000000e+00 - 1.60000000e+01 8.00700000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 7.31900000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 6.99700000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 7.05000000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 7.72400000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 7 -! ------------------------------------------------------------------------------ -0.7 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -16.7538872411828 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --16.7538872411828 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -1.0075 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --1.0075 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0085 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -103 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -9.32600000e-01 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -8.86700000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -8.87700000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -9.15000000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -9.64800000e-01 1.96000000e-01 0.00000000e+00 --1.50000000e+01 -9.93800000e-01 1.02000000e-01 0.00000000e+00 --1.40000000e+01 -1.01750000e+00 2.45000000e-02 0.00000000e+00 --1.30000000e+01 -1.02890000e+00 2.23000000e-02 0.00000000e+00 --1.20000000e+01 -1.02450000e+00 2.02000000e-02 0.00000000e+00 --1.10000000e+01 -9.97300000e-01 1.83000000e-02 0.00000000e+00 --1.00000000e+01 -9.54100000e-01 1.66000000e-02 0.00000000e+00 --9.00000000e+00 -8.90400000e-01 1.50000000e-02 0.00000000e+00 --8.00000000e+00 -8.15600000e-01 1.36000000e-02 0.00000000e+00 --7.00000000e+00 -7.29100000e-01 1.23000000e-02 0.00000000e+00 --6.00000000e+00 -6.32800000e-01 1.12000000e-02 0.00000000e+00 --5.00000000e+00 -5.50000000e-01 1.02000000e-02 0.00000000e+00 --4.00000000e+00 -4.40000000e-01 9.60000000e-03 0.00000000e+00 --3.00000000e+00 -3.30000000e-01 9.10000000e-03 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 8.80000000e-03 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 8.70000000e-03 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 8.50000000e-03 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 8.70000000e-03 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 8.80000000e-03 0.00000000e+00 - 3.00000000e+00 3.30000000e-01 9.10000000e-03 0.00000000e+00 - 4.00000000e+00 4.40000000e-01 9.60000000e-03 0.00000000e+00 - 5.00000000e+00 5.50000000e-01 1.02000000e-02 0.00000000e+00 - 6.00000000e+00 6.32800000e-01 1.12000000e-02 0.00000000e+00 - 7.00000000e+00 7.29100000e-01 1.23000000e-02 0.00000000e+00 - 8.00000000e+00 8.15600000e-01 1.36000000e-02 0.00000000e+00 - 9.00000000e+00 8.90400000e-01 1.50000000e-02 0.00000000e+00 - 1.00000000e+01 9.54100000e-01 1.66000000e-02 0.00000000e+00 - 1.10000000e+01 9.97300000e-01 1.83000000e-02 0.00000000e+00 - 1.20000000e+01 1.02450000e+00 2.02000000e-02 0.00000000e+00 - 1.30000000e+01 1.02890000e+00 2.23000000e-02 0.00000000e+00 - 1.40000000e+01 1.01750000e+00 2.45000000e-02 0.00000000e+00 - 1.50000000e+01 9.93800000e-01 1.02000000e-01 0.00000000e+00 - 1.60000000e+01 9.64800000e-01 1.96000000e-01 0.00000000e+00 - 1.80000000e+01 9.15000000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 8.87700000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 8.86700000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 9.32600000e-01 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 8 -! ------------------------------------------------------------------------------ -1.0 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --1.0573 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -103 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -1.01070000e+00 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -9.69600000e-01 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -9.70700000e-01 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -9.95900000e-01 2.38000000e-01 0.00000000e+00 --1.60000000e+01 -1.04020000e+00 1.08000000e-01 0.00000000e+00 --1.50000000e+01 -1.06240000e+00 2.51000000e-02 0.00000000e+00 --1.40000000e+01 -1.07930000e+00 2.27000000e-02 0.00000000e+00 --1.30000000e+01 -1.08040000e+00 2.06000000e-02 0.00000000e+00 --1.20000000e+01 -1.06640000e+00 1.87000000e-02 0.00000000e+00 --1.10000000e+01 -1.02840000e+00 1.70000000e-02 0.00000000e+00 --1.00000000e+01 -9.75100000e-01 1.54000000e-02 0.00000000e+00 --9.00000000e+00 -9.06700000e-01 1.39000000e-02 0.00000000e+00 --8.00000000e+00 -8.25600000e-01 1.26000000e-02 0.00000000e+00 --7.00000000e+00 -7.36200000e-01 1.15000000e-02 0.00000000e+00 --6.00000000e+00 -6.60000000e-01 1.02000000e-02 0.00000000e+00 --5.00000000e+00 -5.50000000e-01 9.50000000e-03 0.00000000e+00 --4.00000000e+00 -4.40000000e-01 8.90000000e-03 0.00000000e+00 --3.00000000e+00 -3.30000000e-01 8.60000000e-03 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 8.30000000e-03 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 8.20000000e-03 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 8.20000000e-03 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 8.20000000e-03 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 8.30000000e-03 0.00000000e+00 - 3.00000000e+00 3.30000000e-01 8.60000000e-03 0.00000000e+00 - 4.00000000e+00 4.40000000e-01 8.90000000e-03 0.00000000e+00 - 5.00000000e+00 5.50000000e-01 9.50000000e-03 0.00000000e+00 - 6.00000000e+00 6.60000000e-01 1.02000000e-02 0.00000000e+00 - 7.00000000e+00 7.36200000e-01 1.15000000e-02 0.00000000e+00 - 8.00000000e+00 8.25600000e-01 1.26000000e-02 0.00000000e+00 - 9.00000000e+00 9.06700000e-01 1.39000000e-02 0.00000000e+00 - 1.00000000e+01 9.75100000e-01 1.54000000e-02 0.00000000e+00 - 1.10000000e+01 1.02840000e+00 1.70000000e-02 0.00000000e+00 - 1.20000000e+01 1.06640000e+00 1.87000000e-02 0.00000000e+00 - 1.30000000e+01 1.08040000e+00 2.06000000e-02 0.00000000e+00 - 1.40000000e+01 1.07930000e+00 2.27000000e-02 0.00000000e+00 - 1.50000000e+01 1.06240000e+00 2.51000000e-02 0.00000000e+00 - 1.60000000e+01 1.04020000e+00 1.08000000e-01 0.00000000e+00 - 1.80000000e+01 9.95900000e-01 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 9.70700000e-01 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 9.69600000e-01 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 1.01070000e+00 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 9 -! ------------------------------------------------------------------------------ -2.0 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --1.151 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -105 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 --1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 --1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 --1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 --1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 --1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 --1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 --1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 --1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 --1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 --9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 --8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 --7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 --6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 --5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 --4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 --3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 - 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 - 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 - 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 - 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 - 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 - 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 - 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 - 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 - 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 - 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 - 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 - 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 - 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 - 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 - 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 - 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 - 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 -! ------------------------------------------------------------------------------ -! data for table 10 -! ------------------------------------------------------------------------------ -5.0 Re - ! Reynolds number in millions -0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. -23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. --1.2617 Cn2 - ! As Cn1 for negative AOAs. -Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] -0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. -0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] -0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ -! Table of aerodynamics coefficients -107 NumAlf - ! Number of data lines in the following table -! Alpha Cl Cd Cm -! (deg) (-) (-) (-) --1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 --1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 --1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 --1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 --1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 --1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 --1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 --1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 --1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 --1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 --1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 --1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 --1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 --1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 --1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 --1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 --1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 --9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 --9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 --8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 --8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 --7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 --7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 --6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 --6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 --5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 --5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 --4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 --4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 --3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 --3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 --2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 --2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 --2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 --1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 --1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 --1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 --1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 --1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 --1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 --1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 --1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 --1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 --1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 --9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 --8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 --7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 --6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 --5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 --4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 --3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 --2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 --1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 - 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 - 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 - 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 - 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 - 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 - 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 - 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 - 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 - 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 - 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 - 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 - 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 - 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 - 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 - 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 - 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 - 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 - 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 - 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 - 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 - 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 - 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 - 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 - 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 - 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 - 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 - 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 - 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 - 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 - 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 - 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 - 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 - 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 - 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 - 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 - 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 - 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 - 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 - 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 - 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 - 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 - 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 - 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 - 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 - 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 - 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 - 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 - 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 - 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 - 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 - 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 - 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 - 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 - 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 - diff --git a/docs/src/literate/airfoils/NACA_0021.csv b/docs/src/literate/airfoils/NACA_0021.csv deleted file mode 100644 index 7079c688..00000000 --- a/docs/src/literate/airfoils/NACA_0021.csv +++ /dev/null @@ -1,37 +0,0 @@ -100.0001,0 -100,0.221 -95,1.412 -90,2.534 -80,4.591 -70,6.412 -60,7.986 -50,9.265 -40,10.156 -30,10.504 -25,10.397 -20,10.04 -15,9.354 -10,8.195 -7.5,7.35 -5,6.221 -2.5,4.576 -1.25,3.315 -0,0 -1.25,-3.315 -2.5,-4.576 -5,-6.221 -7.5,-7.35 -10,-8.195 -15,-9.354 -20,-10.04 -25,-10.397 -30,-10.504 -40,-10.156 -50,-9.265 -60,-7.986 -70,-6.412 -80,-4.591 -90,-2.534 -95,-1.412 -100,-0.221 -100.0001,0 \ No newline at end of file diff --git a/docs/src/literate/airfoils/NACA_0021.dat b/docs/src/literate/airfoils/NACA_0021.dat deleted file mode 100644 index 086fb2f0..00000000 --- a/docs/src/literate/airfoils/NACA_0021.dat +++ /dev/null @@ -1,1211 +0,0 @@ -Title: NACA0021 -Thickness to Chord Ratio: 0.21 -Zero Lift AOA (deg): 0.0 -Reverse Camber Direction: 0 - -Reynolds Number: 1e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.453900000000000 0.405000000000000 0 --22 -0.300200000000000 0.329000000000000 0 --20 -0.200600000000000 0.282000000000000 0 --18 -0.103500000000000 0.238000000000000 0 --16 -0.0123000000000000 0.196000000000000 0 --14 0.0658000000000000 0.158000000000000 0 --12 0.127600000000000 0.123000000000000 0 --10 0.158100000000000 0.0750000000000000 0 --9 0.158100000000000 0.0575000000000000 0 --8 0.147500000000000 0.0538000000000000 0 --7 0.140000000000000 0.0507000000000000 0 --6 0.124000000000000 0.0480000000000000 0 --5 0.115600000000000 0.0459000000000000 0 --4 0.0995000000000000 0.0441000000000000 0 --3 0.0854000000000000 0.0429000000000000 0 --2 0.0631000000000000 0.0420000000000000 0 --1 0.0320000000000000 0.0414000000000000 0 -0 0 0.0413000000000000 0 -1 -0.0320000000000000 0.0414000000000000 0 -2 -0.0631000000000000 0.0420000000000000 0 -3 -0.0854000000000000 0.0429000000000000 0 -4 -0.0995000000000000 0.0441000000000000 0 -5 -0.115600000000000 0.0459000000000000 0 -6 -0.124000000000000 0.0480000000000000 0 -7 -0.140000000000000 0.0507000000000000 0 -8 -0.147500000000000 0.0538000000000000 0 -9 -0.158100000000000 0.0575000000000000 0 -10 -0.158100000000000 0.0750000000000000 0 -12 -0.127600000000000 0.123000000000000 0 -14 -0.0658000000000000 0.158000000000000 0 -16 0.0123000000000000 0.196000000000000 0 -18 0.103500000000000 0.238000000000000 0 -20 0.200600000000000 0.282000000000000 0 -22 0.300200000000000 0.329000000000000 0 -25 0.453900000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 2e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 1.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -1.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.461800000000000 0.405000000000000 0 --22 -0.310300000000000 0.329000000000000 0 --20 -0.212400000000000 0.282000000000000 0 --18 -0.118000000000000 0.238000000000000 0 --16 -0.0331000000000000 0.196000000000000 0 --14 0.0362000000000000 0.158000000000000 0 --12 0.0713000000000000 0.123000000000000 0 --10 0.0506000000000000 0.0700000000000000 0 --9 0.0190000000000000 0.0435000000000000 0 --8 -0.0120000000000000 0.0407000000000000 0 --7 -0.0266000000000000 0.0382000000000000 0 --6 -0.0475000000000000 0.0362000000000000 0 --5 -0.0505000000000000 0.0345000000000000 0 --4 -0.0619000000000000 0.0332000000000000 0 --3 -0.0472000000000000 0.0321000000000000 0 --2 -0.0393000000000000 0.0314000000000000 0 --1 -0.0243000000000000 0.0310000000000000 0 -0 0 0.0309000000000000 0 -1 0.0243000000000000 0.0310000000000000 0 -2 0.0393000000000000 0.0314000000000000 0 -3 0.0472000000000000 0.0321000000000000 0 -4 0.0619000000000000 0.0332000000000000 0 -5 0.0505000000000000 0.0345000000000000 0 -6 0.0475000000000000 0.0362000000000000 0 -7 0.0266000000000000 0.0382000000000000 0 -8 0.0120000000000000 0.0407000000000000 0 -9 -0.0190000000000000 0.0435000000000000 0 -10 -0.0506000000000000 0.0700000000000000 0 -12 -0.0713000000000000 0.123000000000000 0 -14 -0.0362000000000000 0.158000000000000 0 -16 0.0331000000000000 0.196000000000000 0 -18 0.118000000000000 0.238000000000000 0 -20 0.212400000000000 0.282000000000000 0 -22 0.310300000000000 0.329000000000000 0 -25 0.461800000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 4e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 3.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -3.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 4.309 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.526 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.526 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.480200000000000 0.405000000000000 0 --22 -0.334500000000000 0.329000000000000 0 --20 -0.241400000000000 0.282000000000000 0 --18 -0.161900000000000 0.238000000000000 0 --16 -0.0981000000000000 0.196000000000000 0 --14 -0.0833000000000000 0.158000000000000 0 --12 -0.166000000000000 0.123000000000000 0 --10 -0.269100000000000 0.0620000000000000 0 --9 -0.316200000000000 0.0343000000000000 0 --8 -0.342000000000000 0.0319000000000000 0 --7 -0.342700000000000 0.0297000000000000 0 --6 -0.338200000000000 0.0279000000000000 0 --5 -0.308600000000000 0.0264000000000000 0 --4 -0.273000000000000 0.0253000000000000 0 --3 -0.210300000000000 0.0243000000000000 0 --2 -0.146500000000000 0.0237000000000000 0 --1 -0.0752000000000000 0.0233000000000000 0 -0 0 0.0232000000000000 0 -1 0.0752000000000000 0.0233000000000000 0 -2 0.146500000000000 0.0237000000000000 0 -3 0.210300000000000 0.0243000000000000 0 -4 0.273000000000000 0.0253000000000000 0 -5 0.308600000000000 0.0264000000000000 0 -6 0.338200000000000 0.0279000000000000 0 -7 0.342700000000000 0.0297000000000000 0 -8 0.342000000000000 0.0319000000000000 0 -9 0.316200000000000 0.0343000000000000 0 -10 0.269100000000000 0.0620000000000000 0 -12 0.166000000000000 0.123000000000000 0 -14 0.0833000000000000 0.158000000000000 0 -16 0.0981000000000000 0.196000000000000 0 -18 0.161900000000000 0.238000000000000 0 -20 0.241400000000000 0.282000000000000 0 -22 0.334500000000000 0.329000000000000 0 -25 0.480200000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 8e4 -BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.277 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 0.829 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -0.829 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.529700000000000 0.405000000000000 0 --22 -0.409100000000000 0.329000000000000 0 --20 -0.347500000000000 0.282000000000000 0 --18 -0.322100000000000 0.238000000000000 0 --16 -0.349900000000000 0.196000000000000 0 --14 -0.429600000000000 0.158000000000000 0 --12 -0.522800000000000 0.123000000000000 0 --11 -0.556400000000000 0.0700000000000000 0 --10 -0.578000000000000 0.0297000000000000 0 --9 -0.587400000000000 0.0273000000000000 0 --8 -0.575100000000000 0.0252000000000000 0 --7 -0.544500000000000 0.0233000000000000 0 --6 -0.495300000000000 0.0217000000000000 0 --5 -0.432400000000000 0.0204000000000000 0 --4 -0.356400000000000 0.0194000000000000 0 --3 -0.273100000000000 0.0186000000000000 0 --2 -0.183900000000000 0.0181000000000000 0 --1 -0.0921000000000000 0.0178000000000000 0 -0 0 0.0177000000000000 0 -1 0.0921000000000000 0.0178000000000000 0 -2 0.183900000000000 0.0181000000000000 0 -3 0.273100000000000 0.0186000000000000 0 -4 0.356400000000000 0.0194000000000000 0 -5 0.432400000000000 0.0204000000000000 0 -6 0.495300000000000 0.0217000000000000 0 -7 0.544500000000000 0.0233000000000000 0 -8 0.575100000000000 0.0252000000000000 0 -9 0.587400000000000 0.0273000000000000 0 -10 0.578000000000000 0.0297000000000000 0 -11 0.556400000000000 0.0700000000000000 0 -12 0.522800000000000 0.123000000000000 0 -14 0.429600000000000 0.158000000000000 0 -16 0.349900000000000 0.196000000000000 0 -18 0.322100000000000 0.238000000000000 0 -20 0.347500000000000 0.282000000000000 0 -22 0.409100000000000 0.329000000000000 0 -25 0.529700000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 1.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 5.371 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.031 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.031 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.666400000000000 0.405000000000000 0 --22 -0.602300000000000 0.329000000000000 0 --20 -0.592000000000000 0.282000000000000 0 --18 -0.609800000000000 0.238000000000000 0 --16 -0.648700000000000 0.196000000000000 0 --14 -0.699300000000000 0.158000000000000 0 --13 -0.725500000000000 0.0860000000000000 0 --12 -0.736300000000000 0.0292000000000000 0 --11 -0.744300000000000 0.0266000000000000 0 --10 -0.737400000000000 0.0243000000000000 0 --9 -0.714800000000000 0.0222000000000000 0 --8 -0.674500000000000 0.0204000000000000 0 --7 -0.620900000000000 0.0187000000000000 0 --6 -0.548600000000000 0.0174000000000000 0 --5 -0.468700000000000 0.0163000000000000 0 --4 -0.380000000000000 0.0155000000000000 0 --3 -0.286100000000000 0.0148000000000000 0 --2 -0.187900000000000 0.0143000000000000 0 --1 -0.0842000000000000 0.0140000000000000 0 -0 0 0.0139000000000000 0 -1 0.0842000000000000 0.0140000000000000 0 -2 0.187900000000000 0.0143000000000000 0 -3 0.286100000000000 0.0148000000000000 0 -4 0.380000000000000 0.0155000000000000 0 -5 0.468700000000000 0.0163000000000000 0 -6 0.548600000000000 0.0174000000000000 0 -7 0.620900000000000 0.0187000000000000 0 -8 0.674500000000000 0.0204000000000000 0 -9 0.714800000000000 0.0222000000000000 0 -10 0.737400000000000 0.0243000000000000 0 -11 0.744300000000000 0.0266000000000000 0 -12 0.736300000000000 0.0292000000000000 0 -13 0.725500000000000 0.0860000000000000 0 -14 0.699300000000000 0.158000000000000 0 -16 0.648700000000000 0.196000000000000 0 -18 0.609800000000000 0.238000000000000 0 -20 0.592000000000000 0.282000000000000 0 -22 0.602300000000000 0.329000000000000 0 -25 0.666400000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 3.6e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 5.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -5.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -0.886600000000000 0.405000000000000 0 --22 -0.845300000000000 0.329000000000000 0 --20 -0.839700000000000 0.282000000000000 0 --18 -0.848900000000000 0.238000000000000 0 --16 -0.871700000000000 0.196000000000000 0 --15 -0.884000000000000 0.104000000000000 0 --14 -0.893700000000000 0.0286000000000000 0 --13 -0.897300000000000 0.0260000000000000 0 --12 -0.893800000000000 0.0237000000000000 0 --11 -0.877900000000000 0.0215000000000000 0 --10 -0.850000000000000 0.0195000000000000 0 --9 -0.802600000000000 0.0178000000000000 0 --8 -0.743400000000000 0.0163000000000000 0 --7 -0.672800000000000 0.0149000000000000 0 --6 -0.589100000000000 0.0138000000000000 0 --5 -0.499800000000000 0.0129000000000000 0 --4 -0.404400000000000 0.0122000000000000 0 --3 -0.302400000000000 0.0117000000000000 0 --2 -0.220000000000000 0.0113000000000000 0 --1 -0.110000000000000 0.0111000000000000 0 -0 0 0.0111000000000000 0 -1 0.110000000000000 0.0111000000000000 0 -2 0.220000000000000 0.0113000000000000 0 -3 0.302400000000000 0.0117000000000000 0 -4 0.404400000000000 0.0122000000000000 0 -5 0.499800000000000 0.0129000000000000 0 -6 0.589100000000000 0.0138000000000000 0 -7 0.672800000000000 0.0149000000000000 0 -8 0.743400000000000 0.0163000000000000 0 -9 0.802600000000000 0.0178000000000000 0 -10 0.850000000000000 0.0195000000000000 0 -11 0.877900000000000 0.0215000000000000 0 -12 0.893800000000000 0.0237000000000000 0 -13 0.897300000000000 0.0260000000000000 0 -14 0.893700000000000 0.0286000000000000 0 -15 0.884000000000000 0.104000000000000 0 -16 0.871700000000000 0.196000000000000 0 -18 0.848900000000000 0.238000000000000 0 -20 0.839700000000000 0.282000000000000 0 -22 0.845300000000000 0.329000000000000 0 -25 0.886600000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 7e5 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.54 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.54 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.03500000000000 0.405000000000000 0 --22 -0.994000000000000 0.329000000000000 0 --20 -0.985800000000000 0.282000000000000 0 --18 -0.991100000000000 0.238000000000000 0 --17 -0.997300000000000 0.125000000000000 0 --16 -1.00560000000000 0.0295000000000000 0 --15 -1.01060000000000 0.0269000000000000 0 --14 -1.01220000000000 0.0244000000000000 0 --13 -1.00200000000000 0.0223000000000000 0 --12 -0.984300000000000 0.0202000000000000 0 --11 -0.954300000000000 0.0184000000000000 0 --10 -0.909100000000000 0.0166000000000000 0 --9 -0.849800000000000 0.0152000000000000 0 --8 -0.780200000000000 0.0138000000000000 0 --7 -0.698800000000000 0.0126000000000000 0 --6 -0.610000000000000 0.0117000000000000 0 --5 -0.514600000000000 0.0109000000000000 0 --4 -0.412800000000000 0.0103000000000000 0 --3 -0.330000000000000 0.00980000000000000 0 --2 -0.220000000000000 0.00960000000000000 0 --1 -0.110000000000000 0.00940000000000000 0 -0 0 0.00940000000000000 0 -1 0.110000000000000 0.00940000000000000 0 -2 0.220000000000000 0.00960000000000000 0 -3 0.330000000000000 0.00980000000000000 0 -4 0.412800000000000 0.0103000000000000 0 -5 0.514600000000000 0.0109000000000000 0 -6 0.610000000000000 0.0117000000000000 0 -7 0.698800000000000 0.0126000000000000 0 -8 0.780200000000000 0.0138000000000000 0 -9 0.849800000000000 0.0152000000000000 0 -10 0.909100000000000 0.0166000000000000 0 -11 0.954300000000000 0.0184000000000000 0 -12 0.984300000000000 0.0202000000000000 0 -13 1.00200000000000 0.0223000000000000 0 -14 1.01220000000000 0.0244000000000000 0 -15 1.01060000000000 0.0269000000000000 0 -16 1.00560000000000 0.0295000000000000 0 -17 0.997300000000000 0.125000000000000 0 -18 0.991100000000000 0.238000000000000 0 -20 0.985800000000000 0.282000000000000 0 -22 0.994000000000000 0.329000000000000 0 -25 1.03500000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 1e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.10180000000000 0.405000000000000 0 --22 -1.06440000000000 0.329000000000000 0 --20 -1.05540000000000 0.282000000000000 0 --18 -1.05880000000000 0.135000000000000 0 --17 -1.06410000000000 0.0300000000000000 0 --16 -1.06900000000000 0.0273000000000000 0 --15 -1.07090000000000 0.0248000000000000 0 --14 -1.06570000000000 0.0226000000000000 0 --13 -1.04920000000000 0.0206000000000000 0 --12 -1.02570000000000 0.0187000000000000 0 --11 -0.986200000000000 0.0170000000000000 0 --10 -0.936400000000000 0.0154000000000000 0 --9 -0.869400000000000 0.0140000000000000 0 --8 -0.793900000000000 0.0128000000000000 0 --7 -0.710200000000000 0.0117000000000000 0 --6 -0.619100000000000 0.0108000000000000 0 --5 -0.519200000000000 0.0101000000000000 0 --4 -0.440000000000000 0.00960000000000000 0 --3 -0.330000000000000 0.00920000000000000 0 --2 -0.220000000000000 0.00900000000000000 0 --1 -0.110000000000000 0.00890000000000000 0 -0 0 0.00890000000000000 0 -1 0.110000000000000 0.00890000000000000 0 -2 0.220000000000000 0.00900000000000000 0 -3 0.330000000000000 0.00920000000000000 0 -4 0.440000000000000 0.00960000000000000 0 -5 0.519200000000000 0.0101000000000000 0 -6 0.619100000000000 0.0108000000000000 0 -7 0.710200000000000 0.0117000000000000 0 -8 0.793900000000000 0.0128000000000000 0 -9 0.869400000000000 0.0140000000000000 0 -10 0.936400000000000 0.0154000000000000 0 -11 0.986200000000000 0.0170000000000000 0 -12 1.02570000000000 0.0187000000000000 0 -13 1.04920000000000 0.0206000000000000 0 -14 1.06570000000000 0.0226000000000000 0 -15 1.07090000000000 0.0248000000000000 0 -16 1.06900000000000 0.0273000000000000 0 -17 1.06410000000000 0.0300000000000000 0 -18 1.05880000000000 0.135000000000000 0 -20 1.05540000000000 0.282000000000000 0 -22 1.06440000000000 0.329000000000000 0 -25 1.10180000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 2e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.65 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.65 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.22300000000000 0.405000000000000 0 --22 -1.18930000000000 0.329000000000000 0 --20 -1.18120000000000 0.282000000000000 0 --19 -1.17970000000000 0.145000000000000 0 --18 -1.18140000000000 0.0285000000000000 0 --17 -1.18240000000000 0.0260000000000000 0 --16 -1.18230000000000 0.0236000000000000 0 --15 -1.17470000000000 0.0215000000000000 0 --14 -1.15800000000000 0.0196000000000000 0 --13 -1.13050000000000 0.0179000000000000 0 --12 -1.09060000000000 0.0162000000000000 0 --11 -1.03980000000000 0.0148000000000000 0 --10 -0.973900000000000 0.0135000000000000 0 --9 -0.898600000000000 0.0124000000000000 0 --8 -0.814300000000000 0.0114000000000000 0 --7 -0.725400000000000 0.0105000000000000 0 --6 -0.626800000000000 0.00980000000000000 0 --5 -0.550000000000000 0.00920000000000000 0 --4 -0.440000000000000 0.00890000000000000 0 --3 -0.330000000000000 0.00860000000000000 0 --2 -0.220000000000000 0.00840000000000000 0 --1 -0.110000000000000 0.00830000000000000 0 -0 0 0.00820000000000000 0 -1 0.110000000000000 0.00830000000000000 0 -2 0.220000000000000 0.00840000000000000 0 -3 0.330000000000000 0.00860000000000000 0 -4 0.440000000000000 0.00890000000000000 0 -5 0.550000000000000 0.00920000000000000 0 -6 0.626800000000000 0.00980000000000000 0 -7 0.725400000000000 0.0105000000000000 0 -8 0.814300000000000 0.0114000000000000 0 -9 0.898600000000000 0.0124000000000000 0 -10 0.973900000000000 0.0135000000000000 0 -11 1.03980000000000 0.0148000000000000 0 -12 1.09060000000000 0.0162000000000000 0 -13 1.13050000000000 0.0179000000000000 0 -14 1.15800000000000 0.0196000000000000 0 -15 1.17470000000000 0.0215000000000000 0 -16 1.18230000000000 0.0236000000000000 0 -17 1.18240000000000 0.0260000000000000 0 -18 1.18140000000000 0.0285000000000000 0 -19 1.17970000000000 0.145000000000000 0 -20 1.18120000000000 0.282000000000000 0 -22 1.18930000000000 0.329000000000000 0 -25 1.22300000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 5e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.76 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.76 -AOA (deg) CL CD Cm25 --180 0 0.0250000000000000 0 --175 0.660000000000000 0.0550000000000000 0 --170 0.850000000000000 0.140000000000000 0 --165 0.680000000000000 0.230000000000000 0 --160 0.635000000000000 0.320000000000000 0 --155 0.670000000000000 0.420000000000000 0 --150 0.770000000000000 0.575000000000000 0 --145 0.900000000000000 0.755000000000000 0 --140 0.980000000000000 0.925000000000000 0 --135 0.930000000000000 1.08500000000000 0 --130 0.850000000000000 1.22500000000000 0 --125 0.760000000000000 1.35000000000000 0 --120 0.670000000000000 1.46500000000000 0 --115 0.575000000000000 1.55500000000000 0 --110 0.450000000000000 1.63500000000000 0 --105 0.320000000000000 1.70000000000000 0 --100 0.185000000000000 1.75000000000000 0 --95 0.0500000000000000 1.78000000000000 0 --90 -0.0900000000000000 1.80000000000000 0 --85 -0.230000000000000 1.80000000000000 0 --80 -0.365000000000000 1.78000000000000 0 --75 -0.500000000000000 1.73500000000000 0 --70 -0.630000000000000 1.66500000000000 0 --65 -0.760000000000000 1.57500000000000 0 --60 -0.875000000000000 1.47000000000000 0 --55 -0.955000000000000 1.34500000000000 0 --50 -1.02000000000000 1.21500000000000 0 --45 -1.05000000000000 1.07500000000000 0 --40 -1.03500000000000 0.920000000000000 0 --35 -0.980000000000000 0.745000000000000 0 --30 -0.855000000000000 0.570000000000000 0 --25 -1.34760000000000 0.405000000000000 0 --22 -1.31300000000000 0.329000000000000 0 --20 -1.30540000000000 0.0293000000000000 0 --19 -1.30660000000000 0.0268000000000000 0 --18 -1.30310000000000 0.0245000000000000 0 --17 -1.29770000000000 0.0224000000000000 0 --16 -1.28600000000000 0.0205000000000000 0 --15 -1.26800000000000 0.0186000000000000 0 --14 -1.24100000000000 0.0170000000000000 0 --13 -1.19790000000000 0.0156000000000000 0 --12 -1.14530000000000 0.0143000000000000 0 --11 -1.07870000000000 0.0132000000000000 0 --10 -1.00490000000000 0.0121000000000000 0 --9 -0.922200000000000 0.0112000000000000 0 --8 -0.833400000000000 0.0104000000000000 0 --7 -0.735400000000000 0.00970000000000000 0 --6 -0.660000000000000 0.00910000000000000 0 --5 -0.550000000000000 0.00860000000000000 0 --4 -0.440000000000000 0.00830000000000000 0 --3 -0.330000000000000 0.00810000000000000 0 --2 -0.220000000000000 0.00790000000000000 0 --1 -0.110000000000000 0.00780000000000000 0 -0 0 0.00780000000000000 0 -1 0.110000000000000 0.00780000000000000 0 -2 0.220000000000000 0.00790000000000000 0 -3 0.330000000000000 0.00810000000000000 0 -4 0.440000000000000 0.00830000000000000 0 -5 0.550000000000000 0.00860000000000000 0 -6 0.660000000000000 0.00910000000000000 0 -7 0.735400000000000 0.00970000000000000 0 -8 0.833400000000000 0.0104000000000000 0 -9 0.922200000000000 0.0112000000000000 0 -10 1.00490000000000 0.0121000000000000 0 -11 1.07870000000000 0.0132000000000000 0 -12 1.14530000000000 0.0143000000000000 0 -13 1.19790000000000 0.0156000000000000 0 -14 1.24100000000000 0.0170000000000000 0 -15 1.26800000000000 0.0186000000000000 0 -16 1.28600000000000 0.0205000000000000 0 -17 1.29770000000000 0.0224000000000000 0 -18 1.30310000000000 0.0245000000000000 0 -19 1.30660000000000 0.0268000000000000 0 -20 1.30540000000000 0.0293000000000000 0 -22 1.31300000000000 0.329000000000000 0 -25 1.34760000000000 0.405000000000000 0 -30 0.855000000000000 0.570000000000000 0 -35 0.980000000000000 0.745000000000000 0 -40 1.03500000000000 0.920000000000000 0 -45 1.05000000000000 1.07500000000000 0 -50 1.02000000000000 1.21500000000000 0 -55 0.955000000000000 1.34500000000000 0 -60 0.875000000000000 1.47000000000000 0 -65 0.760000000000000 1.57500000000000 0 -70 0.630000000000000 1.66500000000000 0 -75 0.500000000000000 1.73500000000000 0 -80 0.365000000000000 1.78000000000000 0 -85 0.230000000000000 1.80000000000000 0 -90 0.0900000000000000 1.80000000000000 0 -95 -0.0500000000000000 1.78000000000000 0 -100 -0.185000000000000 1.75000000000000 0 -105 -0.320000000000000 1.70000000000000 0 -110 -0.450000000000000 1.63500000000000 0 -115 -0.575000000000000 1.55500000000000 0 -120 -0.670000000000000 1.46500000000000 0 -125 -0.760000000000000 1.35000000000000 0 -130 -0.850000000000000 1.22500000000000 0 -135 -0.930000000000000 1.08500000000000 0 -140 -0.980000000000000 0.925000000000000 0 -145 -0.900000000000000 0.755000000000000 0 -150 -0.770000000000000 0.575000000000000 0 -155 -0.670000000000000 0.420000000000000 0 -160 -0.635000000000000 0.320000000000000 0 -165 -0.680000000000000 0.230000000000000 0 -170 -0.850000000000000 0.140000000000000 0 -175 -0.660000000000000 0.0550000000000000 0 -180 0 0.0250000000000000 0 - -Reynolds Number: 8e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 10.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -10.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.131 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.82 -LB Dyn. 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Stall Model - Negative Critical Lift Coeff.: -1.21 -AOA (deg) CL CD Cm25 --180.090000000000 -0.00580000000000000 0.0171000000000000 0 --175.090000000000 0.186200000000000 0.0308000000000000 0 --170.010000000000 0.659500000000000 0.0871000000000000 0 --165.020000000000 0.483400000000000 0.195500000000000 0 --160 0.479600000000000 0.272600000000000 0 --154.980000000000 0.552700000000000 0.384000000000000 0 --149.910000000000 0.709900000000000 0.571500000000000 0 --144.890000000000 0.860600000000000 0.804300000000000 0 --139.950000000000 0.916100000000000 0.994800000000000 0 --134.940000000000 0.890000000000000 1.14290000000000 0 --129.930000000000 0.897600000000000 1.35270000000000 0 --124.920000000000 0.823200000000000 1.49910000000000 0 --119.910000000000 0.742900000000000 1.64450000000000 0 --114.990000000000 0.633000000000000 1.75570000000000 0 --109.990000000000 0.507700000000000 1.84560000000000 0 --105.020000000000 0.370600000000000 1.96190000000000 0 --100.050000000000 0.214400000000000 1.99800000000000 0 --95.0400000000000 0.0548000000000000 2.02590000000000 0 --89.9500000000000 -0.114800000000000 2.05020000000000 0 --84.9400000000000 -0.277200000000000 2.02580000000000 0 --79.9600000000000 -0.436900000000000 1.99620000000000 0 --74.9800000000000 -0.576300000000000 1.90700000000000 0 --70 -0.723200000000000 1.84870000000000 0 --65.0600000000000 -0.846200000000000 1.73830000000000 0 --60.0700000000000 -0.957900000000000 1.62890000000000 0 --55.0800000000000 -1.03890000000000 1.49210000000000 0 --50.1000000000000 -1.09710000000000 1.33070000000000 0 --45.1000000000000 -1.13710000000000 1.18230000000000 0 --40.1600000000000 -1.11780000000000 0.995900000000000 0 --35.1500000000000 -1.03810000000000 0.790000000000000 0 --30.1200000000000 -0.893000000000000 0.584000000000000 0 --27.1500000000000 -0.806500000000000 0.478500000000000 0 --25.1000000000000 -0.716400000000000 0.401100000000000 0 --24.1100000000000 -0.676900000000000 0.368900000000000 0 --23.1200000000000 -0.639500000000000 0.338500000000000 0 --22.1000000000000 -0.609900000000000 0.312500000000000 0 --21.0700000000000 -0.596500000000000 0.295000000000000 0 --20.0900000000000 -0.555300000000000 0.266400000000000 0 --19.1300000000000 -0.549200000000000 0.252300000000000 0 --18.0600000000000 -0.550300000000000 0.237300000000000 0 --17.1000000000000 -0.568900000000000 0.224400000000000 0 --16.1200000000000 -0.654400000000000 0.220800000000000 0 --15.1400000000000 -0.787600000000000 0.203400000000000 0 --14.1500000000000 -0.846300000000000 0.159400000000000 0 --13.0900000000000 -0.916500000000000 0.106400000000000 0 --12.1000000000000 -0.924700000000000 0.0781000000000000 0 --11.1100000000000 -0.870800000000000 0.0667000000000000 0 --10.1100000000000 -0.766000000000000 0.0356000000000000 0 --9.05000000000000 -0.736100000000000 0.0263000000000000 0 --8.06000000000000 -0.710900000000000 0.0223000000000000 0 --7.04000000000000 -0.674800000000000 0.0173000000000000 0 --6.01000000000000 -0.614900000000000 0.0155000000000000 0 --5.02000000000000 -0.550000000000000 0.0109000000000000 0 --4.04000000000000 -0.444300000000000 0.0108000000000000 0 --3.01000000000000 -0.331100000000000 0.0109000000000000 0 --2 -0.225000000000000 0.0108000000000000 0 --1 -0.110000000000000 0.0109000000000000 0 -0 0 0.0110000000000000 0 -1 0.110000000000000 0.0109000000000000 0 -2 0.225000000000000 0.0108000000000000 0 -3.01000000000000 0.331100000000000 0.0109000000000000 0 -4.04000000000000 0.444300000000000 0.0108000000000000 0 -5.02000000000000 0.550000000000000 0.0109000000000000 0 -6.01000000000000 0.614900000000000 0.0155000000000000 0 -7.04000000000000 0.674800000000000 0.0173000000000000 0 -8.06000000000000 0.710900000000000 0.0223000000000000 0 -9.05000000000000 0.736100000000000 0.0263000000000000 0 -10.1100000000000 0.766000000000000 0.0356000000000000 0 -11.1100000000000 0.870800000000000 0.0667000000000000 0 -12.1000000000000 0.924700000000000 0.0781000000000000 0 -13.0900000000000 0.916500000000000 0.106400000000000 0 -14.1500000000000 0.846300000000000 0.159400000000000 0 -15.1400000000000 0.787600000000000 0.203400000000000 0 -16.1200000000000 0.654400000000000 0.220800000000000 0 -17.1000000000000 0.568900000000000 0.224400000000000 0 -18.0600000000000 0.550300000000000 0.237300000000000 0 -19.1300000000000 0.549200000000000 0.252300000000000 0 -20.0900000000000 0.555300000000000 0.266400000000000 0 -21.0700000000000 0.596500000000000 0.295000000000000 0 -22.1000000000000 0.609900000000000 0.312500000000000 0 -23.1200000000000 0.639500000000000 0.338500000000000 0 -24.1100000000000 0.676900000000000 0.368900000000000 0 -25.1000000000000 0.716400000000000 0.401100000000000 0 -27.1500000000000 0.806500000000000 0.478500000000000 0 -30.1200000000000 0.893000000000000 0.584000000000000 0 -35.1500000000000 1.03810000000000 0.790000000000000 0 -40.1600000000000 1.11780000000000 0.995900000000000 0 -45.1000000000000 1.13710000000000 1.18230000000000 0 -50.1000000000000 1.09710000000000 1.33070000000000 0 -55.0800000000000 1.03890000000000 1.49210000000000 0 -60.0700000000000 0.957900000000000 1.62890000000000 0 -65.0600000000000 0.846200000000000 1.73830000000000 0 -70 0.723200000000000 1.84870000000000 0 -74.9800000000000 0.576300000000000 1.90700000000000 0 -79.9600000000000 0.436900000000000 1.99620000000000 0 -84.9400000000000 0.277200000000000 2.02580000000000 0 -89.9500000000000 0.114800000000000 2.05020000000000 0 -95.0400000000000 -0.0548000000000000 2.02590000000000 0 -100.050000000000 -0.214400000000000 1.99800000000000 0 -105.020000000000 -0.370600000000000 1.96190000000000 0 -109.990000000000 -0.507700000000000 1.84560000000000 0 -114.990000000000 -0.633000000000000 1.75570000000000 0 -119.910000000000 -0.742900000000000 1.64450000000000 0 -124.920000000000 -0.823200000000000 1.49910000000000 0 -129.930000000000 -0.897600000000000 1.35270000000000 0 -134.940000000000 -0.890000000000000 1.14290000000000 0 -139.950000000000 -0.916100000000000 0.994800000000000 0 -144.890000000000 -0.860600000000000 0.804300000000000 0 -149.910000000000 -0.709900000000000 0.571500000000000 0 -154.980000000000 -0.552700000000000 0.384000000000000 0 -160 -0.479600000000000 0.272600000000000 0 -165.020000000000 -0.483400000000000 0.195500000000000 0 -170.010000000000 -0.659500000000000 0.0871000000000000 0 -175.090000000000 -0.186200000000000 0.0308000000000000 0 -180.090000000000 0.00580000000000000 0.0171000000000000 0 - -Reynolds Number: 1e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.73 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.4 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.4 -AOA (deg) CL CD Cm25 --180.090000000000 -0.00910000000000000 0.0160000000000000 0 --175.100000000000 0.0655000000000000 0.0227000000000000 0 --170.010000000000 0.568700000000000 0.0740000000000000 0 --165.080000000000 0.468500000000000 0.200900000000000 0 --160 0.461300000000000 0.269700000000000 0 --154.980000000000 0.552100000000000 0.388600000000000 0 --149.900000000000 0.735600000000000 0.592300000000000 0 --144.910000000000 0.844800000000000 0.792500000000000 0 --139.950000000000 0.893600000000000 0.976600000000000 0 --134.940000000000 0.888200000000000 1.13810000000000 0 --129.930000000000 0.860900000000000 1.30410000000000 0 --124.920000000000 0.801600000000000 1.45680000000000 0 --119.920000000000 0.719900000000000 1.59540000000000 0 --114.990000000000 0.618300000000000 1.71480000000000 0 --109.990000000000 0.497200000000000 1.82630000000000 0 --105.020000000000 0.356500000000000 1.89120000000000 0 --100.050000000000 0.207700000000000 1.95950000000000 0 --95.0300000000000 0.0525000000000000 2.00190000000000 0 --89.9400000000000 -0.110400000000000 1.98920000000000 0 --84.9800000000000 -0.267500000000000 1.98510000000000 0 --79.9600000000000 -0.425000000000000 1.94780000000000 0 --74.9900000000000 -0.567800000000000 1.87500000000000 0 --70 -0.713300000000000 1.81720000000000 0 --65.0600000000000 -0.834000000000000 1.71920000000000 0 --60.0600000000000 -0.940200000000000 1.60170000000000 0 --55.1100000000000 -1.02110000000000 1.46370000000000 0 --50.1000000000000 -1.07830000000000 1.31380000000000 0 --45.1100000000000 -1.09810000000000 1.14230000000000 0 --40.1300000000000 -1.09800000000000 0.976500000000000 0 --35.1600000000000 -1.01460000000000 0.772800000000000 0 --30.1200000000000 -0.893200000000000 0.580600000000000 0 --28.1500000000000 -0.852900000000000 0.518800000000000 0 --27.1500000000000 -0.818700000000000 0.482400000000000 0 --26.1000000000000 -0.783000000000000 0.446500000000000 0 --25.1000000000000 -0.724200000000000 0.403300000000000 0 --24.1200000000000 -0.646800000000000 0.353400000000000 0 --23.1200000000000 -0.612000000000000 0.325700000000000 0 --22.1000000000000 -0.549500000000000 0.286600000000000 0 --21.0700000000000 -0.538300000000000 0.270800000000000 0 --20.1300000000000 -0.532600000000000 0.258100000000000 0 --19.0800000000000 -0.526800000000000 0.244500000000000 0 --18.0600000000000 -0.524600000000000 0.232100000000000 0 --17.1000000000000 -0.520900000000000 0.219000000000000 0 --16.1200000000000 -0.529300000000000 0.205200000000000 0 --15.1400000000000 -0.710000000000000 0.209400000000000 0 --14.1500000000000 -0.796800000000000 0.174100000000000 0 --13.0800000000000 -0.859200000000000 0.122500000000000 0 --12.1000000000000 -0.910900000000000 0.0821000000000000 0 --11.1100000000000 -0.904500000000000 0.0535000000000000 0 --10.1000000000000 -0.805700000000000 0.0368000000000000 0 --9.06000000000000 -0.734100000000000 0.0265000000000000 0 --8.06000000000000 -0.715400000000000 0.0206000000000000 0 --7.04000000000000 -0.681400000000000 0.0165000000000000 0 --6.01000000000000 -0.619000000000000 0.0139000000000000 0 --5.02000000000000 -0.542600000000000 0.0109000000000000 0 --4.04000000000000 -0.461300000000000 0.00940000000000000 0 --3.02000000000000 -0.346100000000000 0.00920000000000000 0 --2 -0.229600000000000 0.00930000000000000 0 --1 -0.117500000000000 0.00950000000000000 0 -0 0 0.00910000000000000 0 -1 0.117500000000000 0.00950000000000000 0 -2 0.229600000000000 0.00930000000000000 0 -3.02000000000000 0.346100000000000 0.00920000000000000 0 -4.04000000000000 0.461300000000000 0.00940000000000000 0 -5.02000000000000 0.542600000000000 0.0109000000000000 0 -6.01000000000000 0.619000000000000 0.0139000000000000 0 -7.04000000000000 0.681400000000000 0.0165000000000000 0 -8.06000000000000 0.715400000000000 0.0206000000000000 0 -9.06000000000000 0.734100000000000 0.0265000000000000 0 -10.1000000000000 0.805700000000000 0.0368000000000000 0 -11.1100000000000 0.904500000000000 0.0535000000000000 0 -12.1000000000000 0.910900000000000 0.0821000000000000 0 -13.0800000000000 0.859200000000000 0.122500000000000 0 -14.1500000000000 0.796800000000000 0.174100000000000 0 -15.1400000000000 0.710000000000000 0.209400000000000 0 -16.1200000000000 0.529300000000000 0.205200000000000 0 -17.1000000000000 0.520900000000000 0.219000000000000 0 -18.0600000000000 0.524600000000000 0.232100000000000 0 -19.0800000000000 0.526800000000000 0.244500000000000 0 -20.1300000000000 0.532600000000000 0.258100000000000 0 -21.0700000000000 0.538300000000000 0.270800000000000 0 -22.1000000000000 0.549500000000000 0.286600000000000 0 -23.1200000000000 0.612000000000000 0.325700000000000 0 -24.1200000000000 0.646800000000000 0.353400000000000 0 -25.1000000000000 0.724200000000000 0.403300000000000 0 -26.1000000000000 0.783000000000000 0.446500000000000 0 -27.1500000000000 0.818700000000000 0.482400000000000 0 -28.1500000000000 0.852900000000000 0.518800000000000 0 -30.1200000000000 0.893200000000000 0.580600000000000 0 -35.1600000000000 1.01460000000000 0.772800000000000 0 -40.1300000000000 1.09800000000000 0.976500000000000 0 -45.1100000000000 1.09810000000000 1.14230000000000 0 -50.1000000000000 1.07830000000000 1.31380000000000 0 -55.1100000000000 1.02110000000000 1.46370000000000 0 -60.0600000000000 0.940200000000000 1.60170000000000 0 -65.0600000000000 0.834000000000000 1.71920000000000 0 -70 0.713300000000000 1.81720000000000 0 -74.9900000000000 0.567800000000000 1.87500000000000 0 -79.9600000000000 0.425000000000000 1.94780000000000 0 -84.9800000000000 0.267500000000000 1.98510000000000 0 -89.9400000000000 0.110400000000000 1.98920000000000 0 -95.0300000000000 -0.0525000000000000 2.00190000000000 0 -100.050000000000 -0.207700000000000 1.95950000000000 0 -105.020000000000 -0.356500000000000 1.89120000000000 0 -109.990000000000 -0.497200000000000 1.82630000000000 0 -114.990000000000 -0.618300000000000 1.71480000000000 0 -119.920000000000 -0.719900000000000 1.59540000000000 0 -124.920000000000 -0.801600000000000 1.45680000000000 0 -129.930000000000 -0.860900000000000 1.30410000000000 0 -134.940000000000 -0.888200000000000 1.13810000000000 0 -139.950000000000 -0.893600000000000 0.976600000000000 0 -144.910000000000 -0.844800000000000 0.792500000000000 0 -149.900000000000 -0.735600000000000 0.592300000000000 0 -154.980000000000 -0.552100000000000 0.388600000000000 0 -160 -0.461300000000000 0.269700000000000 0 -165.080000000000 -0.468500000000000 0.200900000000000 0 -170.010000000000 -0.568700000000000 0.0740000000000000 0 -175.100000000000 -0.0655000000000000 0.0227000000000000 0 -180.090000000000 0.00910000000000000 0.0160000000000000 0 - -Reynolds Number: 1.5e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 4.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -4.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.451 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.35 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.35 -AOA (deg) CL CD Cm25 --180.080000000000 -0.00830000000000000 0.0151000000000000 0 --175.090000000000 0.0100000000000000 0.0226000000000000 0 --169.950000000000 0.574700000000000 0.0774000000000000 0 --165.040000000000 0.496300000000000 0.217800000000000 0 --159.990000000000 0.465600000000000 0.283500000000000 0 --154.960000000000 0.577700000000000 0.411400000000000 0 --149.900000000000 0.743800000000000 0.609300000000000 0 --144.880000000000 0.838700000000000 0.795600000000000 0 --139.940000000000 0.901500000000000 0.987600000000000 0 --134.930000000000 0.886400000000000 1.14160000000000 0 --129.950000000000 0.857000000000000 1.29850000000000 0 --124.910000000000 0.802900000000000 1.46040000000000 0 --119.950000000000 0.805500000000000 1.65790000000000 0 --115.020000000000 0.687600000000000 1.77070000000000 0 --110.020000000000 0.548300000000000 1.85290000000000 0 --105.040000000000 0.403300000000000 1.92880000000000 0 --100.080000000000 0.244100000000000 1.96500000000000 0 --95.0900000000000 0.0821000000000000 1.99660000000000 0 --89.9700000000000 -0.0863000000000000 1.99630000000000 0 --84.9800000000000 -0.247900000000000 1.98720000000000 0 --80 -0.406200000000000 1.94430000000000 0 --75.0200000000000 -0.556600000000000 1.88990000000000 0 --70.0400000000000 -0.691400000000000 1.79820000000000 0 --65.0800000000000 -0.817900000000000 1.70570000000000 0 --60.1300000000000 -0.922900000000000 1.58220000000000 0 --55.1400000000000 -1.00090000000000 1.43740000000000 0 --50.0900000000000 -1.06080000000000 1.29200000000000 0 --45.0900000000000 -1.06880000000000 1.11120000000000 0 --40.1400000000000 -1.08680000000000 0.967000000000000 0 --35.1500000000000 -1.03340000000000 0.784100000000000 0 --30.1200000000000 -0.939800000000000 0.606800000000000 0 --27.1400000000000 -0.820100000000000 0.482300000000000 0 --25.1000000000000 -0.733100000000000 0.406600000000000 0 --23.1100000000000 -0.647100000000000 0.340500000000000 0 --22.0800000000000 -0.573900000000000 0.298600000000000 0 --20.1200000000000 -0.543900000000000 0.263000000000000 0 --18.0500000000000 -0.519500000000000 0.230900000000000 0 --17.1000000000000 -0.522300000000000 0.221000000000000 0 --16.1200000000000 -0.527300000000000 0.207500000000000 0 --15.1300000000000 -0.713000000000000 0.205900000000000 0 --14.1400000000000 -0.785300000000000 0.172700000000000 0 --13.0800000000000 -0.853500000000000 0.124400000000000 0 --12.1000000000000 -0.912400000000000 0.0818000000000000 0 --11.1000000000000 -0.920600000000000 0.0602000000000000 0 --10.1300000000000 -0.868200000000000 0.0273000000000000 0 --9.06000000000000 -0.759500000000000 0.0212000000000000 0 --8.06000000000000 -0.732100000000000 0.0154000000000000 0 --7.03000000000000 -0.699500000000000 0.0144000000000000 0 --6 -0.634500000000000 0.0118000000000000 0 --5.02000000000000 -0.545400000000000 0.00980000000000000 0 --4.04000000000000 -0.466400000000000 0.00770000000000000 0 --3.02000000000000 -0.349400000000000 0.00760000000000000 0 --2.01000000000000 -0.235300000000000 0.00700000000000000 0 --1.04000000000000 -0.117100000000000 0.00630000000000000 0 -0 0 0.00620000000000000 0 -1.04000000000000 0.117100000000000 0.00630000000000000 0 -2.01000000000000 0.235300000000000 0.00700000000000000 0 -3.02000000000000 0.349400000000000 0.00760000000000000 0 -4.04000000000000 0.466400000000000 0.00770000000000000 0 -5.02000000000000 0.545400000000000 0.00980000000000000 0 -6 0.634500000000000 0.0118000000000000 0 -7.03000000000000 0.699500000000000 0.0144000000000000 0 -8.06000000000000 0.732100000000000 0.0154000000000000 0 -9.06000000000000 0.759500000000000 0.0212000000000000 0 -10.1300000000000 0.868200000000000 0.0273000000000000 0 -11.1000000000000 0.920600000000000 0.0602000000000000 0 -12.1000000000000 0.912400000000000 0.0818000000000000 0 -13.0800000000000 0.853500000000000 0.124400000000000 0 -14.1400000000000 0.785300000000000 0.172700000000000 0 -15.1300000000000 0.713000000000000 0.205900000000000 0 -16.1200000000000 0.527300000000000 0.207500000000000 0 -17.1000000000000 0.522300000000000 0.221000000000000 0 -18.0500000000000 0.519500000000000 0.230900000000000 0 -20.1200000000000 0.543900000000000 0.263000000000000 0 -22.0800000000000 0.573900000000000 0.298600000000000 0 -23.1100000000000 0.647100000000000 0.340500000000000 0 -25.1000000000000 0.733100000000000 0.406600000000000 0 -27.1400000000000 0.820100000000000 0.482300000000000 0 -30.1200000000000 0.939800000000000 0.606800000000000 0 -35.1500000000000 1.03340000000000 0.784100000000000 0 -40.1400000000000 1.08680000000000 0.967000000000000 0 -45.0900000000000 1.06880000000000 1.11120000000000 0 -50.0900000000000 1.06080000000000 1.29200000000000 0 -55.1400000000000 1.00090000000000 1.43740000000000 0 -60.1300000000000 0.922900000000000 1.58220000000000 0 -65.0800000000000 0.817900000000000 1.70570000000000 0 -70.0400000000000 0.691400000000000 1.79820000000000 0 -75.0200000000000 0.556600000000000 1.88990000000000 0 -80 0.406200000000000 1.94430000000000 0 -84.9800000000000 0.247900000000000 1.98720000000000 0 -89.9700000000000 0.0863000000000000 1.99630000000000 0 -95.0900000000000 -0.0821000000000000 1.99660000000000 0 -100.080000000000 -0.244100000000000 1.96500000000000 0 -105.040000000000 -0.403300000000000 1.92880000000000 0 -110.020000000000 -0.548300000000000 1.85290000000000 0 -115.020000000000 -0.687600000000000 1.77070000000000 0 -119.950000000000 -0.805500000000000 1.65790000000000 0 -124.910000000000 -0.802900000000000 1.46040000000000 0 -129.950000000000 -0.857000000000000 1.29850000000000 0 -134.930000000000 -0.886400000000000 1.14160000000000 0 -139.940000000000 -0.901500000000000 0.987600000000000 0 -144.880000000000 -0.838700000000000 0.795600000000000 0 -149.900000000000 -0.743800000000000 0.609300000000000 0 -154.960000000000 -0.577700000000000 0.411400000000000 0 -159.990000000000 -0.465600000000000 0.283500000000000 0 -165.040000000000 -0.496300000000000 0.217800000000000 0 -169.950000000000 -0.574700000000000 0.0774000000000000 0 -175.090000000000 -0.0100000000000000 0.0226000000000000 0 -180.080000000000 0.00830000000000000 0.0151000000000000 0 - -Reynolds Number: 1.8e6 -BV Dyn. Stall Model - Positive Stall AOA (deg): 6.0 -BV Dyn. Stall Model - Negative Stall AOA (deg): -6.0 -LB Dyn. Stall Model - Lift Coeff. Slope at Zero Lift AOA (per radian): 6.303 -LB Dyn. Stall Model - Positive Critical Lift Coeff.: 1.32 -LB Dyn. Stall Model - Negative Critical Lift Coeff.: -1.32 -AOA (deg) CL CD Cm25 --180.080000000000 -0.00830000000000000 0.0151000000000000 0 --175.090000000000 0.0100000000000000 0.0226000000000000 0 --169.950000000000 0.574700000000000 0.0774000000000000 0 --165.040000000000 0.496300000000000 0.217800000000000 0 --159.990000000000 0.465600000000000 0.283500000000000 0 --154.960000000000 0.577700000000000 0.411400000000000 0 --149.900000000000 0.743800000000000 0.609300000000000 0 --144.880000000000 0.838700000000000 0.795600000000000 0 --139.940000000000 0.901500000000000 0.987600000000000 0 --134.930000000000 0.886400000000000 1.14160000000000 0 --129.950000000000 0.857000000000000 1.29850000000000 0 --124.910000000000 0.802900000000000 1.46040000000000 0 --119.950000000000 0.805500000000000 1.65790000000000 0 --115.020000000000 0.687600000000000 1.77070000000000 0 --110.020000000000 0.548300000000000 1.85290000000000 0 --105.040000000000 0.403300000000000 1.92880000000000 0 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a/docs/src/reference/reference.md +++ b/docs/src/reference/reference.md @@ -10,5 +10,5 @@ CurrentModule = OWENS ## Types and functions ```@autodocs -Modules = [OWENS] +Modules = [OWENS,OWENS.OWENSAero,OWENS.OWENSFEA,OWENS.OWENSOpenFASTWrappers,OWENS.OWENSPreComp] ``` \ No newline at end of file diff --git a/examples/SNL34m/SNL34m_Inputs.yml b/examples/SNL34m/SNL34m_Inputs.yml index 5317e990..fcac4630 100644 --- a/examples/SNL34m/SNL34m_Inputs.yml +++ b/examples/SNL34m/SNL34m_Inputs.yml @@ -30,7 +30,7 @@ controlParameters: AeroParameters: Nslices: 35 # number of OWENSAero discritizations #TODO: AD parameters ntheta: 30 # number of OWENSAero azimuthal discretizations - AModel: DMS # AD, DMS, AC + AModel: AD # AD, DMS, AC adi_lib: nothing adi_rootname: "/SNL34m" diff --git a/examples/SNL34m/figs/.gitignore b/examples/SNL34m/figs/.gitignore new file mode 100644 index 00000000..a1363379 --- /dev/null +++ b/examples/SNL34m/figs/.gitignore @@ -0,0 +1 @@ +*.pdf diff --git a/docs/src/literate/airfoils/NACA_0018_Coords.txt b/examples/dev/airfoils/NACA_0018.txt similarity index 100% rename from docs/src/literate/airfoils/NACA_0018_Coords.txt rename to examples/dev/airfoils/NACA_0018.txt diff --git a/docs/src/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl similarity index 86% rename from docs/src/literate/A_simplyRunningOWENS.jl rename to examples/literate/A_simplyRunningOWENS.jl index 285d13c9..eb986002 100644 --- a/docs/src/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -21,8 +21,8 @@ import OWENS -runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] +runpath = path = runpath = joinpath(@__DIR__, "examples", "literate") #splitdir(@__FILE__)[1] -Inp = OWENS.MasterInput("/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate/sampleOWENS.yml") +Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") OWENS.runOWENS(Inp,runpath) \ No newline at end of file diff --git a/docs/src/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl similarity index 98% rename from docs/src/literate/B_detailedInputs.jl rename to examples/literate/B_detailedInputs.jl index 2da08541..8023aa5b 100644 --- a/docs/src/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -17,8 +17,7 @@ import OWENS import OWENSAero # import PyPlot - -path = runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] +path = runpath = joinpath(@__DIR__, "examples", "literate") Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") @@ -111,6 +110,8 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A NuMad_geom_xlscsv_file_strut, NuMad_mat_xlscsv_file_strut, Htwr_base=towerHeight, + strut_twr_mountpoint = [0.25,0.75], + strut_bld_mountpoint = [0.25,0.75], ntelem, nbelem, ncelem, diff --git a/docs/src/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl similarity index 99% rename from docs/src/literate/C_customizablePreprocessing.jl rename to examples/literate/C_customizablePreprocessing.jl index acfee8aa..3cefc8f1 100644 --- a/docs/src/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -22,7 +22,7 @@ import PyPlot import OWENSOpenFASTWrappers -path = runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] +path = runpath = joinpath(@__DIR__, "examples", "literate") Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/examples/literate/airfoils/NACA_0018.txt b/examples/literate/airfoils/NACA_0018.txt new file mode 100644 index 00000000..39bdb98e --- /dev/null +++ b/examples/literate/airfoils/NACA_0018.txt @@ -0,0 +1,208 @@ + 201 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +! x-y coordinate of airfoil reference +! x/c y/c + 0.277853 0 +! coordinates of airfoil shape +! interpolation to 200 points +! x/c y/c + 1.00000000000000e+00 7.40293088030186e-03 + 9.89671379974747e-01 5.52312701646428e-03 + 9.64477131182153e-01 2.48535959199292e-03 + 9.39158624174899e-01 1.50473515887706e-03 + 9.13813162279310e-01 2.76632310473288e-03 + 8.88553591831403e-01 2.67289317456605e-03 + 8.63480304357990e-01 1.25212903431862e-03 + 8.38670008821752e-01 -1.30558063733301e-03 + 8.14184038980280e-01 -4.88132537219822e-03 + 7.90073507481042e-01 -9.41733442728799e-03 + 7.66396243180071e-01 -1.48824286806251e-02 + 7.43171762127060e-01 -2.11375614462018e-02 + 7.20393063763985e-01 -2.79720058036821e-02 + 6.98115514389012e-01 -3.52505652104797e-02 + 6.76338951051125e-01 -4.28545172802418e-02 + 6.54963698148296e-01 -5.06468535065558e-02 + 6.33966484340103e-01 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3.87063242925100e-01 7.4e-03 + 4.03697484944282e-01 7.4e-03 + 4.20727347071592e-01 7.4e-03 + 4.38151752431921e-01 7.4e-03 + 4.55964245711291e-01 7.4e-03 + 4.74161067405196e-01 7.4e-03 + 4.92733472564726e-01 7.4e-03 + 5.11676517362321e-01 7.4e-03 + 5.30985351170107e-01 7.4e-03 + 5.50653338799897e-01 7.4e-03 + 5.70668704030238e-01 7.4e-03 + 5.91022299396154e-01 7.4e-03 + 6.11704971014609e-01 7.4e-03 + 6.32703405878887e-01 7.4e-03 + 6.54007799159681e-01 7.4e-03 + 6.75603313526683e-01 7.4e-03 + 6.97479344035197e-01 7.4e-03 + 7.19619100665882e-01 7.4e-03 + 7.42007863814197e-01 7.4e-03 + 7.64633916307294e-01 7.4e-03 + 7.87480347506928e-01 7.4e-03 + 8.10530974553361e-01 7.4e-03 + 8.33766686857151e-01 7.4e-03 + 8.57171368568559e-01 7.4e-03 + 8.80727606307419e-01 7.4e-03 + 9.04416064906437e-01 7.4e-03 + 9.28217017828997e-01 7.4e-03 + 9.52108466170963e-01 7.4e-03 + 9.76048832000119e-01 7.4e-03 + 1.00000000000000e+00 7.4e-03 diff --git a/docs/src/literate/airfoils/circular.csv b/examples/literate/airfoils/circular.csv similarity index 100% rename from docs/src/literate/airfoils/circular.csv rename to examples/literate/airfoils/circular.csv diff --git a/docs/src/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv b/examples/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv similarity index 76% rename from docs/src/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv rename to examples/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv index 6ad6c14d..390ee9d7 100644 --- a/docs/src/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv +++ b/examples/literate/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv @@ -1,24 +1,24 @@ SNL_5MW_D_Carbon_LCDT,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, ,,,,,,# of segments ->,12,Material ID ->,1,2,4,1,1,2,4,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps -1,0,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -2,6.607,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -3,13.215,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -4,19.822,NACA_0021,sharp,0,5.498,0.3,0.2,,11,1,8,12,11,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -5,26.43,NACA_0021,sharp,0,4.431,0.3,0.2,,9,1,7,10,9,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -6,33.037,NACA_0021,sharp,0,3.806,0.3,0.2,,8,1,6,8,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -7,39.645,NACA_0021,sharp,0,3.435,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -8,46.252,NACA_0021,sharp,0,3.205,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -9,52.859,NACA_0021,sharp,0,3.068,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -10,59.467,NACA_0021,sharp,0,3.003,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -11,66.074,NACA_0021,sharp,0,3,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -12,72.682,NACA_0021,sharp,0,3.056,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -13,79.289,NACA_0021,sharp,0,3.176,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -14,85.896,NACA_0021,sharp,0,3.377,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -15,92.504,NACA_0021,sharp,0,3.688,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -16,99.111,NACA_0021,sharp,0,4.18,0.3,0.2,,8,1,6,9,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -17,105.719,NACA_0021,sharp,0,4.924,0.3,0.2,,10,1,7,11,10,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -18,112.326,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -19,118.934,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -20,125.541,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -21,132.148,NACA_0021,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +1,0,NACA_0018,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,6.607,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,13.215,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,19.822,NACA_0018,sharp,0,5.498,0.3,0.2,,11,1,8,12,11,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +5,26.43,NACA_0018,sharp,0,4.431,0.3,0.2,,9,1,7,10,9,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +6,33.037,NACA_0018,sharp,0,3.806,0.3,0.2,,8,1,6,8,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +7,39.645,NACA_0018,sharp,0,3.435,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +8,46.252,NACA_0018,sharp,0,3.205,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +9,52.859,NACA_0018,sharp,0,3.068,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +10,59.467,NACA_0018,sharp,0,3.003,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +11,66.074,NACA_0018,sharp,0,3,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +12,72.682,NACA_0018,sharp,0,3.056,0.3,0.2,,6,1,4,7,6,1,4,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +13,79.289,NACA_0018,sharp,0,3.176,0.3,0.2,,6,1,5,7,6,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +14,85.896,NACA_0018,sharp,0,3.377,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +15,92.504,NACA_0018,sharp,0,3.688,0.3,0.2,,7,1,5,8,7,1,5,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +16,99.111,NACA_0018,sharp,0,4.18,0.3,0.2,,8,1,6,9,8,1,6,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +17,105.719,NACA_0018,sharp,0,4.924,0.3,0.2,,10,1,7,11,10,1,7,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +18,112.326,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +19,118.934,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +20,125.541,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +21,132.148,NACA_0018,sharp,0,6,0.3,0.2,,12,1,9,13,12,1,9,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/docs/src/literate/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv b/examples/literate/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv similarity index 100% rename from docs/src/literate/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv rename to examples/literate/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv diff --git a/docs/src/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv b/examples/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv similarity index 84% rename from docs/src/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv rename to examples/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv index bf5eeb96..80a1c3bc 100644 --- a/docs/src/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv +++ b/examples/literate/data/NuMAD_Geom_SNL_5MW_Struts.csv @@ -1,7 +1,7 @@ SNL_5MW_D_Carbon_LCDT,,,,# Shear webs ->,1,# of stacks ->,7,Stack ID ->,1,2,3,4,5,6,7,Segment ID ->,1,2,3,4,5,6,7,8,9,10,11,12,DP Types,1,2,3,4,5,6,7,8,9,10,11,12,1,2,3,4,5,6,7,8,9,10,11,12,, ,,,,,,# of segments ->,12,Material ID ->,1,2,4,1,1,2,4,,,,,,,,,,,,,,,,,,,,,,,,,,,first entry in the CSV list is the exterior blade surface stack,,,,,,,,,,,,SW1, Sta.#,Blade span (m),Airfoil Shape File,TE Type,Twist (deg),Chord,xoffset,aero center,Section Label,LE,Panel_Face,Panel_Core,Spar,TE,SW_Face,SW_Core,-blank-,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,,,,,,,,,,,,,,HP_TE,HP_Aft_Panel,HP_Aft_Spar,HP_Fore_Spar,HP_Fore_Panel,HP_LE,LP_LE,LP_Fore_Panel,LP_Aft_Spar,LP_Fore_Spar,LP_Aft_Panel,LP_TE,stacks,dps -1,0,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -2,6.607,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -3,13.215,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" -4,19.822,NACA_0021,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +1,0,NACA_0018,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +2,6.607,NACA_0018,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +3,13.215,NACA_0018,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" +4,19.822,NACA_0018,sharp,0,6,0.3,0.2,,12,1,8,12,12,1,8,-1,-0.95,-0.5,-0.3,-0.1,-0.095,0,0.095,0.1,0.3,0.5,0.95,1,,,,,,,,,,,,,,"2,5,2","2,3,2","2,4,2","2,4,2","2,3,2","2,1,2","2,1,2","2,3,2","2,4,2","2,4,2","2,3,2","2,5,2","6,7,6","9,3,3,9" diff --git a/docs/src/literate/data/NuMAD_Materials_SNL_5MW.csv b/examples/literate/data/NuMAD_Materials_SNL_5MW.csv similarity index 100% rename from docs/src/literate/data/NuMAD_Materials_SNL_5MW.csv rename to examples/literate/data/NuMAD_Materials_SNL_5MW.csv diff --git a/docs/src/literate/sampleOWENS.yml b/examples/literate/sampleOWENS.yml similarity index 94% rename from docs/src/literate/sampleOWENS.yml rename to examples/literate/sampleOWENS.yml index 9e646677..3aaa3239 100644 --- a/docs/src/literate/sampleOWENS.yml +++ b/examples/literate/sampleOWENS.yml @@ -30,15 +30,15 @@ controlParameters: AeroParameters: Nslices: 30 # number of OWENSAero discritizations #TODO: AD parameters ntheta: 30 # number of OWENSAero azimuthal discretizations - AModel: DMS # AD, DMS, AC + AModel: AD # AD, DMS, AC adi_lib: nothing adi_rootname: "/ExampleB" structuralParameters: structuralModel: GX #GX, TNB, ROM nonlinear: false #TODO: propogate - ntelem: 10 #tower elements in each - nbelem: 60 #blade elements in each + ntelem: 20 #tower elements in each + nbelem: 50 #blade elements in each ncelem: 10 #central cable elements in each if turbineType is ARCUS nselem: 5 #strut elements in each if turbineType has struts NuMad_geom_xlscsv_file_twr: /data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv From 542baacb3e53ea852a068500d2f177ea79c9d4d0 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 09:39:53 -0600 Subject: [PATCH 02/11] Add sample DLC run --- examples/literate/A_simplyRunningOWENS.jl | 39 +++++- examples/literate/B_detailedInputs.jl | 2 +- .../literate/C_customizablePreprocessing.jl | 2 +- examples/literate/sampleOWENS.yml | 2 +- src/topRunDLC.jl | 122 ++++++++++++++++-- 5 files changed, 152 insertions(+), 15 deletions(-) diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index eb986002..fbabc480 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -21,8 +21,43 @@ import OWENS -runpath = path = runpath = joinpath(@__DIR__, "examples", "literate") #splitdir(@__FILE__)[1] +runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") -OWENS.runOWENS(Inp,runpath) \ No newline at end of file +OWENS.runOWENS(Inp,runpath) + +simulated_time = 2.0 #seconds + DLCs = ["1_1"] #"normal" +# DLCs = ["1_3"] #"normal" +# DLCs = ["1_4"] #"normal" +# DLCs = ["1_5"] #"normal" +# DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" +# DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" +# DLCs = ["3_1"] #"startup" +# DLCs = ["3_2"] #"startup" +# DLCs = ["3_3"] #"startup" +# DLCs = ["4_1"] #"shutdown" +# DLCs = ["4_2"] #"shutdown" +# DLCs = ["5_1"] #"emergencyshutdown" +# DLCs = ["6_1"] #"parked" +# DLCs = ["6_2"] #"parked_idle" +# DLCs = ["6_4"] #"parked" +# DLCs = ["7_1"] #"parked" +# DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] + + +OWENS.runDLC(DLCs,Inp,runpath; + IEC_std="\"1-ED3\"", + WindChar="\"A\"", + WindClass=1, + NumGrid_Z=38, + NumGrid_Y=26, + Vdesign=11.0, + grid_oversize=1.25, + Vinf_range=[10.0],#LinRange(4,24,21), + regenWindFiles=false, + delta_t_turbsim=0.05, + simtime_turbsim=30.0, + pathtoturbsim="$localpath/../openfast/build/modules/turbsim/turbsim", + runScript=OWENS.runOWENS) diff --git a/examples/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl index 8023aa5b..c5f8fbe9 100644 --- a/examples/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -17,7 +17,7 @@ import OWENS import OWENSAero # import PyPlot -path = runpath = joinpath(@__DIR__, "examples", "literate") +path = runpath = splitdir(@__FILE__)[1]#splitdir(@__FILE__)[1]#joinpath(@__DIR__, "examples", "literate") Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index 3cefc8f1..da157272 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -22,7 +22,7 @@ import PyPlot import OWENSOpenFASTWrappers -path = runpath = joinpath(@__DIR__, "examples", "literate") +path = runpath = splitdir(@__FILE__)[1]#joinpath(@__DIR__, "examples", "literate") Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/examples/literate/sampleOWENS.yml b/examples/literate/sampleOWENS.yml index 3aaa3239..551484c5 100644 --- a/examples/literate/sampleOWENS.yml +++ b/examples/literate/sampleOWENS.yml @@ -21,7 +21,7 @@ turbulentInflow: ifw_libfile: nothing controlParameters: - controlStrategy: constantRPM # TODO: incorporate the others + controlStrategy: normal # TODO: incorporate the others RPM: 17.2 #RPM numTS: 100 # delta_t: 0.01 # s diff --git a/src/topRunDLC.jl b/src/topRunDLC.jl index 3c2dc435..d0867421 100644 --- a/src/topRunDLC.jl +++ b/src/topRunDLC.jl @@ -284,15 +284,68 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A AD15On = false end + # Handle the control strategy + + normalRPM = RPM + slowRPM = 1.0 #RPM + tocp = [0.0,10.0,30.0,1000.0] + turbineStartup = 0 + generatorOn = false + useGeneratorFunction = false + throwawayTimeSteps=1#round(Int,10.0/delta_t) # 10 seconds + if controlStrategy == "normal" + Omegaocp = [normalRPM,normalRPM,normalRPM,normalRPM]./60 #hz + turbineStartup = 0 + generatorOn = false + useGeneratorFunction = false + elseif controlStrategy == "freewheelatNormalOperatingRPM" + Omegaocp = [normalRPM,normalRPM,normalRPM,normalRPM]./60 #hz + turbineStartup = 2 + generatorOn = false + useGeneratorFunction = false + elseif controlStrategy == "startup" + throwawayTimeSteps = 1 + tocp = [0.0,30.0,1000.0] + Omegaocp = [slowRPM,normalRPM,normalRPM]./60 #hz + turbineStartup = 0 + generatorOn = false + useGeneratorFunction = false + elseif controlStrategy == "shutdown" + tocp = [0.0,10.0,15.0,30.0,1000.0] + Omegaocp = [normalRPM,normalRPM,normalRPM/2,slowRPM,0.0]./60 #hz + elseif controlStrategy == "emergencyshutdown" + tocp = [0.0,10.0,15.0,30.0,1000.0] + Omegaocp = [normalRPM,normalRPM,slowRPM,0.0,0.0]./60 #hz + elseif controlStrategy == "parked" + Omegaocp = [slowRPM,slowRPM,slowRPM,slowRPM]./60 #hz + elseif controlStrategy == "parked_idle" + Omegaocp = [slowRPM,slowRPM,slowRPM,slowRPM]./60 #hz + turbineStartup = 2 + generatorOn = false + useGeneratorFunction = false + elseif controlStrategy == "parked_yaw" + Omegaocp = [slowRPM,slowRPM,slowRPM,slowRPM]./60 #hz + elseif controlStrategy == "parked" + Omegaocp = [slowRPM,slowRPM,slowRPM,slowRPM]./60 #hz + elseif controlStrategy == "transport" + Omegaocp = [slowRPM,slowRPM,slowRPM,slowRPM]./60 #hz + end + + println("controlStrategy: $controlStrategy") + inputs = OWENS.Inputs(;analysisType = structuralModel, - tocp = [0.0,100000.1], - Omegaocp = [RPM,RPM] ./ 60, + tocp, + Omegaocp, tocp_Vinf = [0.0,100000.1], Vinfocp = [Vinf,Vinf], numTS, delta_t, AD15On, - aeroLoadsOn = 2) + aeroLoadsOn = 2, + turbineStartup, + generatorOn, + useGeneratorFunction, + OmegaInit = Omegaocp[1]) nothing @@ -303,7 +356,8 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A joint = myjoint, platformTurbineConnectionNodeNumber = 1, pBC, - nlOn = true, + nlOn = false, + gravityOn = true, numNodes = mymesh.numNodes, RayleighAlpha = 0.05, RayleighBeta = 0.05, @@ -317,7 +371,8 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A println("Running Unsteady") t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, - epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, + epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FPtfmHist,FHydroHist,FMooringHist, + topFexternal_hist,rbDataHist = OWENS.Unsteady_Land(inputs;system,assembly, topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) nothing @@ -326,8 +381,11 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function and: TODO - println("Saving VTK time domain files") - OWENS.OWENSFEA_VTK("$path/vtk/SNLARCUS5MW_timedomain_TNBnltrue",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) + azi=aziHist#./aziHist*1e-6 + saveName = "$path/vtk/SNL5MW" + OWENS.OWENSVTK(saveName,t,uHist,system,assembly,sections,aziHist,mymesh,myel, + epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist, + FReactionHist,topFexternal_hist;tsave_idx) nothing @@ -340,18 +398,62 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, - topstrainout_tower_U,topstrainout_tower_LtopDamage_blade_U, + topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, - mymesh,myel,myort,Nbld,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, + mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5, LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5, Twr_LE_U_idx=1,Twr_LE_L_idx=1, AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) #TODO: add in ability to have material safety factors and load safety factors - return [1.0,2.0,3.0] + dataDumpFilename = "$path/InitialDataOutputs.h5" + + HDF5.h5open(dataDumpFilename, "w") do file + HDF5.write(file,"t",collect(t)) + HDF5.write(file,"aziHist",aziHist) + HDF5.write(file,"OmegaHist",OmegaHist) + HDF5.write(file,"OmegaDotHist",OmegaDotHist) + HDF5.write(file,"gbHist",gbHist) + HDF5.write(file,"gbDotHist",gbDotHist) + HDF5.write(file,"gbDotDotHist",gbDotDotHist) + HDF5.write(file,"FReactionHist",FReactionHist) + HDF5.write(file,"FTwrBsHist",FTwrBsHist) + HDF5.write(file,"genTorque",genTorque) + HDF5.write(file,"genPower",genPower) + HDF5.write(file,"torqueDriveShaft",torqueDriveShaft) + HDF5.write(file,"uHist",uHist) + HDF5.write(file,"uHist_prp",uHist_prp) + HDF5.write(file,"epsilon_x_hist",epsilon_x_hist) + HDF5.write(file,"epsilon_y_hist",epsilon_y_hist) + HDF5.write(file,"epsilon_z_hist",epsilon_z_hist) + HDF5.write(file,"kappa_x_hist",kappa_x_hist) + HDF5.write(file,"kappa_y_hist",kappa_y_hist) + HDF5.write(file,"kappa_z_hist",kappa_z_hist) + HDF5.write(file,"massOwens",massOwens) + HDF5.write(file,"stress_U",stress_U) + HDF5.write(file,"SF_ult_U",SF_ult_U) + HDF5.write(file,"SF_buck_U",SF_buck_U) + HDF5.write(file,"stress_L",stress_L) + HDF5.write(file,"SF_ult_L",SF_ult_L) + HDF5.write(file,"SF_buck_L",SF_buck_L) + HDF5.write(file,"stress_TU",stress_TU) + HDF5.write(file,"SF_ult_TU",SF_ult_TU) + HDF5.write(file,"SF_buck_TU",SF_buck_TU) + HDF5.write(file,"stress_TL",stress_TL) + HDF5.write(file,"SF_ult_TL",SF_ult_TL) + HDF5.write(file,"SF_buck_TL",SF_buck_TL) + HDF5.write(file,"topstrainout_blade_U",topstrainout_blade_U) + HDF5.write(file,"topstrainout_blade_L",topstrainout_blade_L) + HDF5.write(file,"topstrainout_tower_U",topstrainout_tower_U) + HDF5.write(file,"topstrainout_tower_L",topstrainout_tower_L) + HDF5.write(file,"topDamage_blade_U",topDamage_blade_U) + HDF5.write(file,"topDamage_blade_L",topDamage_blade_L) + HDF5.write(file,"topDamage_tower_U",topDamage_tower_U) + HDF5.write(file,"topDamage_tower_L",topDamage_tower_L) + end end From b2d453f133a28f465a5a0be1148a894c7875278b Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 10:25:49 -0600 Subject: [PATCH 03/11] Update paths to work for automated deployment of docs --- docs/Project.toml | 6 +++ examples/literate/A_simplyRunningOWENS.jl | 45 +++++++++++-------- examples/literate/B_detailedInputs.jl | 2 +- .../literate/C_customizablePreprocessing.jl | 2 +- src/topRunDLC.jl | 8 +++- 5 files changed, 40 insertions(+), 23 deletions(-) diff --git a/docs/Project.toml b/docs/Project.toml index e3f07f6c..2df429d0 100644 --- a/docs/Project.toml +++ b/docs/Project.toml @@ -1,8 +1,14 @@ [deps] BenchmarkTools = "6e4b80f9-dd63-53aa-95a3-0cdb28fa8baf" +Composites = "d0d699f6-c662-11e8-0fb1-1b30104ab829" Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4" FLOWMath = "6cb5d3fb-0fe8-4cc2-bd89-9fe0b19a99d3" Literate = "98b081ad-f1c9-55d3-8b20-4c87d4299306" +OWENS = "51d15398-4eaf-40f9-a029-79ae1c4a3867" +OWENSAero = "ac8500f8-acb1-479a-8630-5dcb97b7c093" +OWENSFEA = "5906b1e7-6737-4278-91ec-d653c88addb4" +OWENSOpenFASTWrappers = "1f4f357c-c864-4b71-8437-d48f9e1bb3e6" +OWENSPreComp = "7fd84261-8b17-47b6-a87d-1cc34e69440e" PyPlot = "d330b81b-6aea-500a-939a-2ce795aea3ee" QuadGK = "1fd47b50-473d-5c70-9696-f719f8f3bcdc" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index fbabc480..e28161a8 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -21,30 +21,35 @@ import OWENS -runpath = path = splitdir(@__FILE__)[1] +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] +#md runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") OWENS.runOWENS(Inp,runpath) +# Here is an example of using the same model against the automated DLC run script. +# Note that for a setup cutom to a specific design, you'll want to go to the B level to get all of the detailed inputs correct +# One of these is the controller where a discon controller library can be coupled instead of the specified RPM control. + simulated_time = 2.0 #seconds DLCs = ["1_1"] #"normal" -# DLCs = ["1_3"] #"normal" -# DLCs = ["1_4"] #"normal" -# DLCs = ["1_5"] #"normal" -# DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" -# DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" -# DLCs = ["3_1"] #"startup" -# DLCs = ["3_2"] #"startup" -# DLCs = ["3_3"] #"startup" -# DLCs = ["4_1"] #"shutdown" -# DLCs = ["4_2"] #"shutdown" -# DLCs = ["5_1"] #"emergencyshutdown" -# DLCs = ["6_1"] #"parked" -# DLCs = ["6_2"] #"parked_idle" -# DLCs = ["6_4"] #"parked" -# DLCs = ["7_1"] #"parked" -# DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] +#md DLCs = ["1_3"] #"normal" +#md DLCs = ["1_4"] #"normal" +#md DLCs = ["1_5"] #"normal" +#md DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" +#md DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" +#md DLCs = ["3_1"] #"startup" +#md DLCs = ["3_2"] #"startup" +#md DLCs = ["3_3"] #"startup" +#md DLCs = ["4_1"] #"shutdown" +#md DLCs = ["4_2"] #"shutdown" +#md DLCs = ["5_1"] #"emergencyshutdown" +#md DLCs = ["6_1"] #"parked" +#md DLCs = ["6_2"] #"parked_idle" +#md DLCs = ["6_4"] #"parked" +#md DLCs = ["7_1"] #"parked" +#md DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] OWENS.runDLC(DLCs,Inp,runpath; @@ -56,8 +61,10 @@ OWENS.runDLC(DLCs,Inp,runpath; Vdesign=11.0, grid_oversize=1.25, Vinf_range=[10.0],#LinRange(4,24,21), - regenWindFiles=false, + regenWindFiles=true, delta_t_turbsim=0.05, simtime_turbsim=30.0, - pathtoturbsim="$localpath/../openfast/build/modules/turbsim/turbsim", + pathtoturbsim="$runpath/../../../OWENSOpenFASTWrappers.jl/deps/openfast/build/modules/turbsim/turbsim", runScript=OWENS.runOWENS) + +nothing \ No newline at end of file diff --git a/examples/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl index c5f8fbe9..1549c05c 100644 --- a/examples/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -17,7 +17,7 @@ import OWENS import OWENSAero # import PyPlot -path = runpath = splitdir(@__FILE__)[1]#splitdir(@__FILE__)[1]#joinpath(@__DIR__, "examples", "literate") +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index da157272..4b4884c7 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -22,7 +22,7 @@ import PyPlot import OWENSOpenFASTWrappers -path = runpath = splitdir(@__FILE__)[1]#joinpath(@__DIR__, "examples", "literate") +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/src/topRunDLC.jl b/src/topRunDLC.jl index d0867421..ba165e6c 100644 --- a/src/topRunDLC.jl +++ b/src/topRunDLC.jl @@ -375,6 +375,10 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A topFexternal_hist,rbDataHist = OWENS.Unsteady_Land(inputs;system,assembly, topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) + if AModel=="AD" + OWENSOpenFASTWrappers.endTurb() + end + nothing # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the @@ -385,7 +389,7 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A saveName = "$path/vtk/SNL5MW" OWENS.OWENSVTK(saveName,t,uHist,system,assembly,sections,aziHist,mymesh,myel, epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist, - FReactionHist,topFexternal_hist;tsave_idx) + FReactionHist,topFexternal_hist) nothing @@ -402,7 +406,7 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, - mymesh,myel,myort,number_of_blades,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, + mymesh,myel,myort,B,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5, LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5, From 7d8f82c1c9700e52a05e310fa530bf8371ada28b Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 10:38:23 -0600 Subject: [PATCH 04/11] Update app example and the documentation toml to accomodate the custom packages installation --- app/OWENS_APP/src/sampleOWENS.yml | 29 +++++++++++++++-------------- app/build_app.sh | 2 +- docs/Project.toml | 5 ----- 3 files changed, 16 insertions(+), 20 deletions(-) diff --git a/app/OWENS_APP/src/sampleOWENS.yml b/app/OWENS_APP/src/sampleOWENS.yml index d7e488e3..a32c40b0 100644 --- a/app/OWENS_APP/src/sampleOWENS.yml +++ b/app/OWENS_APP/src/sampleOWENS.yml @@ -17,11 +17,11 @@ operationParameters: turbulentInflow: ifw: false WindType: 3 - wind_filename: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/turbsim/115mx115m_30x30_20.0msETM.bts - ifw_libfile: ./../openfast/build/modules/inflowwind/libifw_c_binding + windINPfilename: /data/turbsim/115mx115m_30x30_20.0msETM.bts + ifw_libfile: /Users/kevmoor/Documents/coderepos/OWENS_Toolkit/OWENSOpenFASTWrappers.jl/deps/openfast/build/modules/inflowwind/libifw_c_binding controlParameters: - controlStrategy: constantRPM # TODO: incorporate the others + controlStrategy: normal # TODO: incorporate the others RPM: 17.2 #RPM numTS: 100 # delta_t: 0.01 # s @@ -30,19 +30,20 @@ controlParameters: AeroParameters: Nslices: 30 # number of OWENSAero discritizations #TODO: AD parameters ntheta: 30 # number of OWENSAero azimuthal discretizations - AModel: AD # AD, DMS, AC - adi_lib: "/Users/kevmoor/Documents/coderepos/openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding" - adi_rootname: "./ExampleB" + AModel: DMS # AD, DMS, AC + adi_lib: /Users/kevmoor/Documents/coderepos/OWENS_Toolkit/OWENSOpenFASTWrappers.jl/deps/openfast/build/modules/aerodyn/libaerodyn_inflow_c_binding + adi_rootname: "/ExampleB" structuralParameters: structuralModel: GX #GX, TNB, ROM - ntelem: 10 #tower elements in each - nbelem: 60 #blade elements in each + nonlinear: false #TODO: propogate + ntelem: 20 #tower elements in each + nbelem: 50 #blade elements in each ncelem: 10 #central cable elements in each if turbineType is ARCUS nselem: 5 #strut elements in each if turbineType has struts - NuMad_geom_xlscsv_file_twr: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv - NuMad_mat_xlscsv_file_twr: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Materials_SNL_5MW.csv - NuMad_geom_xlscsv_file_bld: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv - NuMad_mat_xlscsv_file_bld: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Materials_SNL_5MW.csv - NuMad_geom_xlscsv_file_strut: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Geom_SNL_5MW_Struts.csv - NuMad_mat_xlscsv_file_strut: /Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/data/NuMAD_Materials_SNL_5MW.csv + NuMad_geom_xlscsv_file_twr: /data/NuMAD_Geom_SNL_5MW_D_TaperedTower.csv + NuMad_mat_xlscsv_file_twr: /data/NuMAD_Materials_SNL_5MW.csv + NuMad_geom_xlscsv_file_bld: /data/NuMAD_Geom_SNL_5MW_D_Carbon_LCDT_ThickFoils_ThinSkin.csv + NuMad_mat_xlscsv_file_bld: /data/NuMAD_Materials_SNL_5MW.csv + NuMad_geom_xlscsv_file_strut: /data/NuMAD_Geom_SNL_5MW_Struts.csv + NuMad_mat_xlscsv_file_strut: /data/NuMAD_Materials_SNL_5MW.csv diff --git a/app/build_app.sh b/app/build_app.sh index ae192de5..41028878 100755 --- a/app/build_app.sh +++ b/app/build_app.sh @@ -1,2 +1,2 @@ julia -e 'using PackageCompiler; create_app("OWENS_APP","OWENS_APP_COMPILED";force=true, incremental=false)' -OWENS_APP_COMPILED/bin/OWENS_APP "/Users/kevmoor/Documents/coderepos/OWENS.jl/app/OWENS_APP/src/" --julia-args -t4 \ No newline at end of file +OWENS_APP_COMPILED/bin/OWENS_APP "/Users/kevmoor/Documents/coderepos/OWENS_Toolkit/OWENS.jl/app/OWENS_APP/src" --julia-args -t4 \ No newline at end of file diff --git a/docs/Project.toml b/docs/Project.toml index 2df429d0..963ceafa 100644 --- a/docs/Project.toml +++ b/docs/Project.toml @@ -4,11 +4,6 @@ Composites = "d0d699f6-c662-11e8-0fb1-1b30104ab829" Documenter = "e30172f5-a6a5-5a46-863b-614d45cd2de4" FLOWMath = "6cb5d3fb-0fe8-4cc2-bd89-9fe0b19a99d3" Literate = "98b081ad-f1c9-55d3-8b20-4c87d4299306" -OWENS = "51d15398-4eaf-40f9-a029-79ae1c4a3867" -OWENSAero = "ac8500f8-acb1-479a-8630-5dcb97b7c093" -OWENSFEA = "5906b1e7-6737-4278-91ec-d653c88addb4" -OWENSOpenFASTWrappers = "1f4f357c-c864-4b71-8437-d48f9e1bb3e6" -OWENSPreComp = "7fd84261-8b17-47b6-a87d-1cc34e69440e" PyPlot = "d330b81b-6aea-500a-939a-2ce795aea3ee" QuadGK = "1fd47b50-473d-5c70-9696-f719f8f3bcdc" ReverseDiff = "37e2e3b7-166d-5795-8a7a-e32c996b4267" From 57638fa5a898e69f7f2601cf0b04bf616d969d16 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 10:50:11 -0600 Subject: [PATCH 05/11] Add missed airfoils --- examples/literate/airfoils/NACA_0018.csv | 37 + examples/literate/airfoils/NACA_0018.dat | 1464 ++++++++++++++++++++++ 2 files changed, 1501 insertions(+) create mode 100644 examples/literate/airfoils/NACA_0018.csv create mode 100644 examples/literate/airfoils/NACA_0018.dat diff --git a/examples/literate/airfoils/NACA_0018.csv b/examples/literate/airfoils/NACA_0018.csv new file mode 100644 index 00000000..c3dc48ef --- /dev/null +++ b/examples/literate/airfoils/NACA_0018.csv @@ -0,0 +1,37 @@ +1.0001, 0.0 +1.0000, 0.00189 +0.9500, 0.01210 +0.9000, 0.02172 +0.8000, 0.03935 +0.7000, 0.05496 +0.6000, 0.06845 +0.5000, 0.07941 +0.4000, 0.08705 +0.3000, 0.09003 +0.2500, 0.08912 +0.2000, 0.08606 +0.1500, 0.08018 +0.1000, 0.07024 +0.0750, 0.06300 +0.0500, 0.05332 +0.0250, 0.03922 +0.0125, 0.02841 +0.0000, 0.00000 +0.0125, -0.02841 +0.0250, -0.03922 +0.0500, -0.05332 +0.0750, -0.06300 +0.1000, -0.07024 +0.1500, -0.08018 +0.2000, -0.08606 +0.2500, -0.08912 +0.3000, -0.09003 +0.4000, -0.08705 +0.5000, -0.07941 +0.6000, -0.06845 +0.7000, -0.05496 +0.8000, -0.03935 +0.9000, -0.02172 +0.9500, -0.01210 +1.0000, -0.00189 +1.0001, 0.0 \ No newline at end of file diff --git a/examples/literate/airfoils/NACA_0018.dat b/examples/literate/airfoils/NACA_0018.dat new file mode 100644 index 00000000..91a33ff6 --- /dev/null +++ b/examples/literate/airfoils/NACA_0018.dat @@ -0,0 +1,1464 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA 0018 at Re = 0.01,0.02,0.04,0.08,0.16,0.36,0.70,1,2,5 million +! line +! line +! ------------------------------------------------------------------------------ +DEFAULT InterpOrd - ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=3] +0.18 RelThickness - ! The non-dimensional thickness of the airfoil (thickness/chord) [only used if UAMod=7] [default=0.2] (-) +1 NonDimArea - ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA_0018.txt" NumCoords - ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"NA" BL_file - ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. +10 NumTabs - ! Number of airfoil tables in this file. Each table must have lines for Re and Ctrl. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ +0.01 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +8.136711569484852 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-8.136711569484852 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.8163 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1482 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.1545 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.77500000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.17200000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.11100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.07000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.05100000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.50000000e-03 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 7.67000000e-02 1.23000000e-01 0.00000000e+00 +-1.10000000e+01 1.12500000e-01 8.00000000e-02 0.00000000e+00 +-1.00000000e+01 1.42300000e-01 5.74000000e-02 0.00000000e+00 +-9.00000000e+00 1.58400000e-01 5.25000000e-02 0.00000000e+00 +-8.00000000e+00 1.50100000e-01 4.89000000e-02 0.00000000e+00 +-7.00000000e+00 1.18200000e-01 4.63000000e-02 0.00000000e+00 +-6.00000000e+00 8.39000000e-02 4.43000000e-02 0.00000000e+00 +-5.00000000e+00 5.77000000e-02 4.25000000e-02 0.00000000e+00 +-4.00000000e+00 3.68000000e-02 4.10000000e-02 0.00000000e+00 +-3.00000000e+00 2.33000000e-02 3.99000000e-02 0.00000000e+00 +-2.00000000e+00 1.54000000e-02 3.91000000e-02 0.00000000e+00 +-1.00000000e+00 4.50000000e-03 3.87000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 3.85000000e-02 0.00000000e+00 + 1.00000000e+00 -4.50000000e-03 3.87000000e-02 0.00000000e+00 + 2.00000000e+00 -1.54000000e-02 3.91000000e-02 0.00000000e+00 + 3.00000000e+00 -2.33000000e-02 3.99000000e-02 0.00000000e+00 + 4.00000000e+00 -3.68000000e-02 4.10000000e-02 0.00000000e+00 + 5.00000000e+00 -5.77000000e-02 4.25000000e-02 0.00000000e+00 + 6.00000000e+00 -8.39000000e-02 4.43000000e-02 0.00000000e+00 + 7.00000000e+00 -1.18200000e-01 4.63000000e-02 0.00000000e+00 + 8.00000000e+00 -1.50100000e-01 4.89000000e-02 0.00000000e+00 + 9.00000000e+00 -1.58400000e-01 5.25000000e-02 0.00000000e+00 + 1.00000000e+01 -1.42300000e-01 5.74000000e-02 0.00000000e+00 + 1.10000000e+01 -1.12500000e-01 8.00000000e-02 0.00000000e+00 + 1.20000000e+01 -7.67000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 8.50000000e-03 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.05100000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.07000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.11100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.17200000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.77500000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 2 +! ------------------------------------------------------------------------------ +0.02 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +9.154276388714532 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-9.154276388714532 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.1809 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.1809 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0286 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.79800000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.19800000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.15100000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.12000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.11400000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -1.72000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 6.02000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 1.00300000e-01 6.30000000e-02 0.00000000e+00 +-9.00000000e+00 6.82000000e-02 3.96000000e-02 0.00000000e+00 +-8.00000000e+00 -2.14000000e-02 3.76000000e-02 0.00000000e+00 +-7.00000000e+00 -1.16100000e-01 3.58000000e-02 0.00000000e+00 +-6.00000000e+00 -1.58200000e-01 3.39000000e-02 0.00000000e+00 +-5.00000000e+00 -1.78800000e-01 3.23000000e-02 0.00000000e+00 +-4.00000000e+00 -1.78800000e-01 3.10000000e-02 0.00000000e+00 +-3.00000000e+00 -1.55000000e-01 2.99000000e-02 0.00000000e+00 +-2.00000000e+00 -1.13500000e-01 2.92000000e-02 0.00000000e+00 +-1.00000000e+00 -6.07000000e-02 2.88000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.86000000e-02 0.00000000e+00 + 1.00000000e+00 6.07000000e-02 2.88000000e-02 0.00000000e+00 + 2.00000000e+00 1.13500000e-01 2.92000000e-02 0.00000000e+00 + 3.00000000e+00 1.55000000e-01 2.99000000e-02 0.00000000e+00 + 4.00000000e+00 1.78800000e-01 3.10000000e-02 0.00000000e+00 + 5.00000000e+00 1.78800000e-01 3.23000000e-02 0.00000000e+00 + 6.00000000e+00 1.58200000e-01 3.39000000e-02 0.00000000e+00 + 7.00000000e+00 1.16100000e-01 3.58000000e-02 0.00000000e+00 + 8.00000000e+00 2.14000000e-02 3.76000000e-02 0.00000000e+00 + 9.00000000e+00 -6.82000000e-02 3.96000000e-02 0.00000000e+00 + 1.00000000e+01 -1.00300000e-01 6.30000000e-02 0.00000000e+00 + 1.20000000e+01 -6.02000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 1.72000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.11400000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.12000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.15100000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.19800000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.79800000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 3 +! ------------------------------------------------------------------------------ +0.04 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +10.299096322309719 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-10.299096322309719 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.4757 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.4757 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0214 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +97 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.84000000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.26500000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.23600000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.22800000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.28700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -4.89000000e-02 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -1.39000000e-02 1.23000000e-01 0.00000000e+00 +-1.00000000e+01 -2.10800000e-01 6.20000000e-02 0.00000000e+00 +-9.00000000e+00 -3.54400000e-01 3.27000000e-02 0.00000000e+00 +-8.00000000e+00 -4.42800000e-01 3.03000000e-02 0.00000000e+00 +-7.00000000e+00 -4.75800000e-01 2.82000000e-02 0.00000000e+00 +-6.00000000e+00 -4.57300000e-01 2.63000000e-02 0.00000000e+00 +-5.00000000e+00 -4.11700000e-01 2.47000000e-02 0.00000000e+00 +-4.00000000e+00 -3.49500000e-01 2.35000000e-02 0.00000000e+00 +-3.00000000e+00 -2.68800000e-01 2.25000000e-02 0.00000000e+00 +-2.00000000e+00 -1.83300000e-01 2.19000000e-02 0.00000000e+00 +-1.00000000e+00 -9.36000000e-02 2.15000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 2.14000000e-02 0.00000000e+00 + 1.00000000e+00 9.36000000e-02 2.15000000e-02 0.00000000e+00 + 2.00000000e+00 1.83300000e-01 2.19000000e-02 0.00000000e+00 + 3.00000000e+00 2.68800000e-01 2.25000000e-02 0.00000000e+00 + 4.00000000e+00 3.49500000e-01 2.35000000e-02 0.00000000e+00 + 5.00000000e+00 4.11700000e-01 2.47000000e-02 0.00000000e+00 + 6.00000000e+00 4.57300000e-01 2.63000000e-02 0.00000000e+00 + 7.00000000e+00 4.75800000e-01 2.82000000e-02 0.00000000e+00 + 8.00000000e+00 4.42800000e-01 3.03000000e-02 0.00000000e+00 + 9.00000000e+00 3.54400000e-01 3.27000000e-02 0.00000000e+00 + 1.00000000e+01 2.10800000e-01 6.20000000e-02 0.00000000e+00 + 1.20000000e+01 1.39000000e-02 1.23000000e-01 0.00000000e+00 + 1.40000000e+01 4.89000000e-02 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 1.28700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.22800000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.23600000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.26500000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.84000000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 4 +! ------------------------------------------------------------------------------ +0.08 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +11.587085702041861 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-11.587085702041861 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.6566 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.6566 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0162 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +99 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -5.96300000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -4.43000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -3.47200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -2.60300000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -2.02700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -2.25600000e-01 1.58000000e-01 0.00000000e+00 +-1.20000000e+01 -4.40800000e-01 8.00000000e-02 0.00000000e+00 +-1.10000000e+01 -5.53100000e-01 3.15000000e-02 0.00000000e+00 +-1.00000000e+01 -6.24800000e-01 2.88000000e-02 0.00000000e+00 +-9.00000000e+00 -6.60600000e-01 2.64000000e-02 0.00000000e+00 +-8.00000000e+00 -6.58900000e-01 2.42000000e-02 0.00000000e+00 +-7.00000000e+00 -6.22400000e-01 2.23000000e-02 0.00000000e+00 +-6.00000000e+00 -5.61500000e-01 2.06000000e-02 0.00000000e+00 +-5.00000000e+00 -4.75300000e-01 1.92000000e-02 0.00000000e+00 +-4.00000000e+00 -3.88000000e-01 1.81000000e-02 0.00000000e+00 +-3.00000000e+00 -2.92400000e-01 1.72000000e-02 0.00000000e+00 +-2.00000000e+00 -1.93500000e-01 1.67000000e-02 0.00000000e+00 +-1.00000000e+00 -8.89000000e-02 1.63000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.62000000e-02 0.00000000e+00 + 1.00000000e+00 8.89000000e-02 1.63000000e-02 0.00000000e+00 + 2.00000000e+00 1.93500000e-01 1.67000000e-02 0.00000000e+00 + 3.00000000e+00 2.92400000e-01 1.72000000e-02 0.00000000e+00 + 4.00000000e+00 3.88000000e-01 1.81000000e-02 0.00000000e+00 + 5.00000000e+00 4.75300000e-01 1.92000000e-02 0.00000000e+00 + 6.00000000e+00 5.61500000e-01 2.06000000e-02 0.00000000e+00 + 7.00000000e+00 6.22400000e-01 2.23000000e-02 0.00000000e+00 + 8.00000000e+00 6.58900000e-01 2.42000000e-02 0.00000000e+00 + 9.00000000e+00 6.60600000e-01 2.64000000e-02 0.00000000e+00 + 1.00000000e+01 6.24800000e-01 2.88000000e-02 0.00000000e+00 + 1.10000000e+01 5.53100000e-01 3.15000000e-02 0.00000000e+00 + 1.20000000e+01 4.40800000e-01 8.00000000e-02 0.00000000e+00 + 1.40000000e+01 2.25600000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 2.02700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 2.60300000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 3.47200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 4.43000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 5.96300000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 5 +! ------------------------------------------------------------------------------ +0.16 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +13.036149081898586 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-13.036149081898586 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.787 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.787 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0128 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -6.32100000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -5.02600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -4.38200000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -4.20200000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -4.89600000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -6.23700000e-01 1.58000000e-01 0.00000000e+00 +-1.30000000e+01 -6.92300000e-01 7.70000000e-02 0.00000000e+00 +-1.20000000e+01 -7.48800000e-01 2.88000000e-02 0.00000000e+00 +-1.10000000e+01 -7.85200000e-01 2.62000000e-02 0.00000000e+00 +-1.00000000e+01 -7.94900000e-01 2.38000000e-02 0.00000000e+00 +-9.00000000e+00 -7.78100000e-01 2.17000000e-02 0.00000000e+00 +-8.00000000e+00 -7.37300000e-01 1.98000000e-02 0.00000000e+00 +-7.00000000e+00 -6.72400000e-01 1.81000000e-02 0.00000000e+00 +-6.00000000e+00 -5.96000000e-01 1.66000000e-02 0.00000000e+00 +-5.00000000e+00 -5.06800000e-01 1.53000000e-02 0.00000000e+00 +-4.00000000e+00 -4.11400000e-01 1.44000000e-02 0.00000000e+00 +-3.00000000e+00 -3.08800000e-01 1.37000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.31000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.29000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.28000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.29000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.31000000e-02 0.00000000e+00 + 3.00000000e+00 3.08800000e-01 1.37000000e-02 0.00000000e+00 + 4.00000000e+00 4.11400000e-01 1.44000000e-02 0.00000000e+00 + 5.00000000e+00 5.06800000e-01 1.53000000e-02 0.00000000e+00 + 6.00000000e+00 5.96000000e-01 1.66000000e-02 0.00000000e+00 + 7.00000000e+00 6.72400000e-01 1.81000000e-02 0.00000000e+00 + 8.00000000e+00 7.37300000e-01 1.98000000e-02 0.00000000e+00 + 9.00000000e+00 7.78100000e-01 2.17000000e-02 0.00000000e+00 + 1.00000000e+01 7.94900000e-01 2.38000000e-02 0.00000000e+00 + 1.10000000e+01 7.85200000e-01 2.62000000e-02 0.00000000e+00 + 1.20000000e+01 7.48800000e-01 2.88000000e-02 0.00000000e+00 + 1.30000000e+01 6.92300000e-01 7.70000000e-02 0.00000000e+00 + 1.40000000e+01 6.23700000e-01 1.58000000e-01 0.00000000e+00 + 1.60000000e+01 4.89600000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 4.20200000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 4.38200000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 5.02600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 6.32100000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 6 +! ------------------------------------------------------------------------------ +0.36 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +14.963057557300898 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-14.963057557300898 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.9125 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-0.9125 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0101 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +101 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -7.72400000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -7.05000000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -6.99700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -7.31900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -8.00700000e-01 1.96000000e-01 0.00000000e+00 +-1.40000000e+01 -8.80300000e-01 9.40000000e-02 0.00000000e+00 +-1.30000000e+01 -9.10400000e-01 2.59000000e-02 0.00000000e+00 +-1.20000000e+01 -9.27900000e-01 2.35000000e-02 0.00000000e+00 +-1.10000000e+01 -9.24900000e-01 2.13000000e-02 0.00000000e+00 +-1.00000000e+01 -8.98300000e-01 1.94000000e-02 0.00000000e+00 +-9.00000000e+00 -8.52600000e-01 1.76000000e-02 0.00000000e+00 +-8.00000000e+00 -7.87900000e-01 1.59000000e-02 0.00000000e+00 +-7.00000000e+00 -7.10000000e-01 1.45000000e-02 0.00000000e+00 +-6.00000000e+00 -6.22800000e-01 1.32000000e-02 0.00000000e+00 +-5.00000000e+00 -5.24000000e-01 1.21000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 1.12000000e-02 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 1.07000000e-02 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 1.04000000e-02 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 1.02000000e-02 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 1.01000000e-02 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 1.02000000e-02 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 1.04000000e-02 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 1.07000000e-02 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 1.12000000e-02 0.00000000e+00 + 5.00000000e+00 5.24000000e-01 1.21000000e-02 0.00000000e+00 + 6.00000000e+00 6.22800000e-01 1.32000000e-02 0.00000000e+00 + 7.00000000e+00 7.10000000e-01 1.45000000e-02 0.00000000e+00 + 8.00000000e+00 7.87900000e-01 1.59000000e-02 0.00000000e+00 + 9.00000000e+00 8.52600000e-01 1.76000000e-02 0.00000000e+00 + 1.00000000e+01 8.98300000e-01 1.94000000e-02 0.00000000e+00 + 1.10000000e+01 9.24900000e-01 2.13000000e-02 0.00000000e+00 + 1.20000000e+01 9.27900000e-01 2.35000000e-02 0.00000000e+00 + 1.30000000e+01 9.10400000e-01 2.59000000e-02 0.00000000e+00 + 1.40000000e+01 8.80300000e-01 9.40000000e-02 0.00000000e+00 + 1.60000000e+01 8.00700000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 7.31900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 6.99700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 7.05000000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 7.72400000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 7 +! ------------------------------------------------------------------------------ +0.7 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +16.7538872411828 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-16.7538872411828 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0075 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0075 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0085 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -9.32600000e-01 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -8.86700000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -8.87700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.15000000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -9.64800000e-01 1.96000000e-01 0.00000000e+00 +-1.50000000e+01 -9.93800000e-01 1.02000000e-01 0.00000000e+00 +-1.40000000e+01 -1.01750000e+00 2.45000000e-02 0.00000000e+00 +-1.30000000e+01 -1.02890000e+00 2.23000000e-02 0.00000000e+00 +-1.20000000e+01 -1.02450000e+00 2.02000000e-02 0.00000000e+00 +-1.10000000e+01 -9.97300000e-01 1.83000000e-02 0.00000000e+00 +-1.00000000e+01 -9.54100000e-01 1.66000000e-02 0.00000000e+00 +-9.00000000e+00 -8.90400000e-01 1.50000000e-02 0.00000000e+00 +-8.00000000e+00 -8.15600000e-01 1.36000000e-02 0.00000000e+00 +-7.00000000e+00 -7.29100000e-01 1.23000000e-02 0.00000000e+00 +-6.00000000e+00 -6.32800000e-01 1.12000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 1.02000000e-02 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 9.60000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 9.10000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.50000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 9.10000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 9.60000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 1.02000000e-02 0.00000000e+00 + 6.00000000e+00 6.32800000e-01 1.12000000e-02 0.00000000e+00 + 7.00000000e+00 7.29100000e-01 1.23000000e-02 0.00000000e+00 + 8.00000000e+00 8.15600000e-01 1.36000000e-02 0.00000000e+00 + 9.00000000e+00 8.90400000e-01 1.50000000e-02 0.00000000e+00 + 1.00000000e+01 9.54100000e-01 1.66000000e-02 0.00000000e+00 + 1.10000000e+01 9.97300000e-01 1.83000000e-02 0.00000000e+00 + 1.20000000e+01 1.02450000e+00 2.02000000e-02 0.00000000e+00 + 1.30000000e+01 1.02890000e+00 2.23000000e-02 0.00000000e+00 + 1.40000000e+01 1.01750000e+00 2.45000000e-02 0.00000000e+00 + 1.50000000e+01 9.93800000e-01 1.02000000e-01 0.00000000e+00 + 1.60000000e+01 9.64800000e-01 1.96000000e-01 0.00000000e+00 + 1.80000000e+01 9.15000000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 8.87700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 8.86700000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 9.32600000e-01 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 8 +! ------------------------------------------------------------------------------ +1.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +17.801185316865297 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-17.801185316865297 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.0573 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.0573 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0082 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +103 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.01070000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -9.69600000e-01 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -9.70700000e-01 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -9.95900000e-01 2.38000000e-01 0.00000000e+00 +-1.60000000e+01 -1.04020000e+00 1.08000000e-01 0.00000000e+00 +-1.50000000e+01 -1.06240000e+00 2.51000000e-02 0.00000000e+00 +-1.40000000e+01 -1.07930000e+00 2.27000000e-02 0.00000000e+00 +-1.30000000e+01 -1.08040000e+00 2.06000000e-02 0.00000000e+00 +-1.20000000e+01 -1.06640000e+00 1.87000000e-02 0.00000000e+00 +-1.10000000e+01 -1.02840000e+00 1.70000000e-02 0.00000000e+00 +-1.00000000e+01 -9.75100000e-01 1.54000000e-02 0.00000000e+00 +-9.00000000e+00 -9.06700000e-01 1.39000000e-02 0.00000000e+00 +-8.00000000e+00 -8.25600000e-01 1.26000000e-02 0.00000000e+00 +-7.00000000e+00 -7.36200000e-01 1.15000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 1.02000000e-02 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 9.50000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.60000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 8.30000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 8.20000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 8.20000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 8.20000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 8.30000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.60000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 9.50000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 1.02000000e-02 0.00000000e+00 + 7.00000000e+00 7.36200000e-01 1.15000000e-02 0.00000000e+00 + 8.00000000e+00 8.25600000e-01 1.26000000e-02 0.00000000e+00 + 9.00000000e+00 9.06700000e-01 1.39000000e-02 0.00000000e+00 + 1.00000000e+01 9.75100000e-01 1.54000000e-02 0.00000000e+00 + 1.10000000e+01 1.02840000e+00 1.70000000e-02 0.00000000e+00 + 1.20000000e+01 1.06640000e+00 1.87000000e-02 0.00000000e+00 + 1.30000000e+01 1.08040000e+00 2.06000000e-02 0.00000000e+00 + 1.40000000e+01 1.07930000e+00 2.27000000e-02 0.00000000e+00 + 1.50000000e+01 1.06240000e+00 2.51000000e-02 0.00000000e+00 + 1.60000000e+01 1.04020000e+00 1.08000000e-01 0.00000000e+00 + 1.80000000e+01 9.95900000e-01 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 9.70700000e-01 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 9.69600000e-01 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.01070000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 9 +! ------------------------------------------------------------------------------ +2.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +20.027374578257152 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-20.027374578257152 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.151 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.151 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0077 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +105 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.14680000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.11270000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.11720000e+00 2.82000000e-01 0.00000000e+00 +-1.80000000e+01 -1.13830000e+00 2.38000000e-01 0.00000000e+00 +-1.70000000e+01 -1.15500000e+00 1.20000000e-01 0.00000000e+00 +-1.60000000e+01 -1.16950000e+00 2.40000000e-02 0.00000000e+00 +-1.50000000e+01 -1.18130000e+00 2.18000000e-02 0.00000000e+00 +-1.40000000e+01 -1.18130000e+00 1.97000000e-02 0.00000000e+00 +-1.30000000e+01 -1.16620000e+00 1.79000000e-02 0.00000000e+00 +-1.20000000e+01 -1.12960000e+00 1.63000000e-02 0.00000000e+00 +-1.10000000e+01 -1.07720000e+00 1.48000000e-02 0.00000000e+00 +-1.00000000e+01 -1.01110000e+00 1.34000000e-02 0.00000000e+00 +-9.00000000e+00 -9.31400000e-01 1.22000000e-02 0.00000000e+00 +-8.00000000e+00 -8.43900000e-01 1.11000000e-02 0.00000000e+00 +-7.00000000e+00 -7.44900000e-01 1.01000000e-02 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 9.30000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.70000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 8.40000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 8.00000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.80000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.70000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.70000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.70000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.80000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 8.00000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 8.40000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.70000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 9.30000000e-03 0.00000000e+00 + 7.00000000e+00 7.44900000e-01 1.01000000e-02 0.00000000e+00 + 8.00000000e+00 8.43900000e-01 1.11000000e-02 0.00000000e+00 + 9.00000000e+00 9.31400000e-01 1.22000000e-02 0.00000000e+00 + 1.00000000e+01 1.01110000e+00 1.34000000e-02 0.00000000e+00 + 1.10000000e+01 1.07720000e+00 1.48000000e-02 0.00000000e+00 + 1.20000000e+01 1.12960000e+00 1.63000000e-02 0.00000000e+00 + 1.30000000e+01 1.16620000e+00 1.79000000e-02 0.00000000e+00 + 1.40000000e+01 1.18130000e+00 1.97000000e-02 0.00000000e+00 + 1.50000000e+01 1.18130000e+00 2.18000000e-02 0.00000000e+00 + 1.60000000e+01 1.16950000e+00 2.40000000e-02 0.00000000e+00 + 1.70000000e+01 1.15500000e+00 1.20000000e-01 0.00000000e+00 + 1.80000000e+01 1.13830000e+00 2.38000000e-01 0.00000000e+00 + 2.00000000e+01 1.11720000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.11270000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.14680000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +! ------------------------------------------------------------------------------ +! data for table 10 +! ------------------------------------------------------------------------------ +5.0 Re - ! Reynolds number in millions +0 Ctrl - ! Control setting (must be 0 for current AirfoilInfo) +True InclUAdata - ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ +0.0 alpha0 - ! 0-lift angle of attack, depends on airfoil. +23.403123375221707 alpha1 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) +-23.403123375221707 alpha2 - ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] +0.0 S2 - ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S3 - ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] +0.0 S4 - ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] +1.2617 Cn1 - ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. +-1.2617 Cn2 - ! As Cn1 for negative AOAs. +Default St_sh - ! Strouhal's shedding frequency constant. [default = 0.19] +0.0073 Cd0 - ! 2D drag coefficient value at 0-lift. +0.0 Cm0 - ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] +0.0 k0 - ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] +0.0 k1 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k2 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k3 - ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] +0.0 k1_hat - ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +Default x_cp_bar - ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +Default UACutout - ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +Default filtCutOff - ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] +!........................................ +! Table of aerodynamics coefficients +107 NumAlf - ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) +-1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 +-1.75000000e+02 6.60000000e-01 5.50000000e-02 0.00000000e+00 +-1.70000000e+02 8.50000000e-01 1.40000000e-01 0.00000000e+00 +-1.65000000e+02 6.80000000e-01 2.30000000e-01 0.00000000e+00 +-1.60000000e+02 6.35000000e-01 3.20000000e-01 0.00000000e+00 +-1.55000000e+02 6.70000000e-01 4.20000000e-01 0.00000000e+00 +-1.50000000e+02 7.70000000e-01 5.75000000e-01 0.00000000e+00 +-1.45000000e+02 9.00000000e-01 7.55000000e-01 0.00000000e+00 +-1.40000000e+02 9.80000000e-01 9.25000000e-01 0.00000000e+00 +-1.35000000e+02 9.30000000e-01 1.08500000e+00 0.00000000e+00 +-1.30000000e+02 8.50000000e-01 1.22500000e+00 0.00000000e+00 +-1.25000000e+02 7.60000000e-01 1.35000000e+00 0.00000000e+00 +-1.20000000e+02 6.70000000e-01 1.46500000e+00 0.00000000e+00 +-1.15000000e+02 5.75000000e-01 1.55500000e+00 0.00000000e+00 +-1.10000000e+02 4.50000000e-01 1.63500000e+00 0.00000000e+00 +-1.05000000e+02 3.20000000e-01 1.70000000e+00 0.00000000e+00 +-1.00000000e+02 1.85000000e-01 1.75000000e+00 0.00000000e+00 +-9.50000000e+01 5.00000000e-02 1.78000000e+00 0.00000000e+00 +-9.00000000e+01 -9.00000000e-02 1.80000000e+00 0.00000000e+00 +-8.50000000e+01 -2.30000000e-01 1.80000000e+00 0.00000000e+00 +-8.00000000e+01 -3.65000000e-01 1.78000000e+00 0.00000000e+00 +-7.50000000e+01 -5.00000000e-01 1.73500000e+00 0.00000000e+00 +-7.00000000e+01 -6.30000000e-01 1.66500000e+00 0.00000000e+00 +-6.50000000e+01 -7.60000000e-01 1.57500000e+00 0.00000000e+00 +-6.00000000e+01 -8.75000000e-01 1.47000000e+00 0.00000000e+00 +-5.50000000e+01 -9.55000000e-01 1.34500000e+00 0.00000000e+00 +-5.00000000e+01 -1.02000000e+00 1.21500000e+00 0.00000000e+00 +-4.50000000e+01 -1.05000000e+00 1.07500000e+00 0.00000000e+00 +-4.00000000e+01 -1.03500000e+00 9.20000000e-01 0.00000000e+00 +-3.50000000e+01 -9.80000000e-01 7.45000000e-01 0.00000000e+00 +-3.00000000e+01 -8.55000000e-01 5.70000000e-01 0.00000000e+00 +-2.50000000e+01 -1.29250000e+00 4.05000000e-01 0.00000000e+00 +-2.20000000e+01 -1.27140000e+00 3.29000000e-01 0.00000000e+00 +-2.00000000e+01 -1.27680000e+00 2.82000000e-01 0.00000000e+00 +-1.90000000e+01 -1.28530000e+00 1.40000000e-01 0.00000000e+00 +-1.80000000e+01 -1.29600000e+00 2.44000000e-02 0.00000000e+00 +-1.70000000e+01 -1.30380000e+00 2.23000000e-02 0.00000000e+00 +-1.60000000e+01 -1.30670000e+00 2.03000000e-02 0.00000000e+00 +-1.50000000e+01 -1.30040000e+00 1.85000000e-02 0.00000000e+00 +-1.40000000e+01 -1.28080000e+00 1.68000000e-02 0.00000000e+00 +-1.30000000e+01 -1.24300000e+00 1.53000000e-02 0.00000000e+00 +-1.20000000e+01 -1.18840000e+00 1.40000000e-02 0.00000000e+00 +-1.10000000e+01 -1.12110000e+00 1.28000000e-02 0.00000000e+00 +-1.00000000e+01 -1.04040000e+00 1.17000000e-02 0.00000000e+00 +-9.00000000e+00 -9.52500000e-01 1.08000000e-02 0.00000000e+00 +-8.00000000e+00 -8.53800000e-01 1.00000000e-02 0.00000000e+00 +-7.00000000e+00 -7.70000000e-01 9.30000000e-03 0.00000000e+00 +-6.00000000e+00 -6.60000000e-01 8.70000000e-03 0.00000000e+00 +-5.00000000e+00 -5.50000000e-01 8.30000000e-03 0.00000000e+00 +-4.00000000e+00 -4.40000000e-01 7.90000000e-03 0.00000000e+00 +-3.00000000e+00 -3.30000000e-01 7.70000000e-03 0.00000000e+00 +-2.00000000e+00 -2.20000000e-01 7.50000000e-03 0.00000000e+00 +-1.00000000e+00 -1.10000000e-01 7.30000000e-03 0.00000000e+00 + 0.00000000e+00 0.00000000e+00 7.30000000e-03 0.00000000e+00 + 1.00000000e+00 1.10000000e-01 7.30000000e-03 0.00000000e+00 + 2.00000000e+00 2.20000000e-01 7.50000000e-03 0.00000000e+00 + 3.00000000e+00 3.30000000e-01 7.70000000e-03 0.00000000e+00 + 4.00000000e+00 4.40000000e-01 7.90000000e-03 0.00000000e+00 + 5.00000000e+00 5.50000000e-01 8.30000000e-03 0.00000000e+00 + 6.00000000e+00 6.60000000e-01 8.70000000e-03 0.00000000e+00 + 7.00000000e+00 7.70000000e-01 9.30000000e-03 0.00000000e+00 + 8.00000000e+00 8.53800000e-01 1.00000000e-02 0.00000000e+00 + 9.00000000e+00 9.52500000e-01 1.08000000e-02 0.00000000e+00 + 1.00000000e+01 1.04040000e+00 1.17000000e-02 0.00000000e+00 + 1.10000000e+01 1.12110000e+00 1.28000000e-02 0.00000000e+00 + 1.20000000e+01 1.18840000e+00 1.40000000e-02 0.00000000e+00 + 1.30000000e+01 1.24300000e+00 1.53000000e-02 0.00000000e+00 + 1.40000000e+01 1.28080000e+00 1.68000000e-02 0.00000000e+00 + 1.50000000e+01 1.30040000e+00 1.85000000e-02 0.00000000e+00 + 1.60000000e+01 1.30670000e+00 2.03000000e-02 0.00000000e+00 + 1.70000000e+01 1.30380000e+00 2.23000000e-02 0.00000000e+00 + 1.80000000e+01 1.29600000e+00 2.44000000e-02 0.00000000e+00 + 1.90000000e+01 1.28530000e+00 1.40000000e-01 0.00000000e+00 + 2.00000000e+01 1.27680000e+00 2.82000000e-01 0.00000000e+00 + 2.20000000e+01 1.27140000e+00 3.29000000e-01 0.00000000e+00 + 2.50000000e+01 1.29250000e+00 4.05000000e-01 0.00000000e+00 + 3.00000000e+01 8.55000000e-01 5.70000000e-01 0.00000000e+00 + 3.50000000e+01 9.80000000e-01 7.45000000e-01 0.00000000e+00 + 4.00000000e+01 1.03500000e+00 9.20000000e-01 0.00000000e+00 + 4.50000000e+01 1.05000000e+00 1.07500000e+00 0.00000000e+00 + 5.00000000e+01 1.02000000e+00 1.21500000e+00 0.00000000e+00 + 5.50000000e+01 9.55000000e-01 1.34500000e+00 0.00000000e+00 + 6.00000000e+01 8.75000000e-01 1.47000000e+00 0.00000000e+00 + 6.50000000e+01 7.60000000e-01 1.57500000e+00 0.00000000e+00 + 7.00000000e+01 6.30000000e-01 1.66500000e+00 0.00000000e+00 + 7.50000000e+01 5.00000000e-01 1.73500000e+00 0.00000000e+00 + 8.00000000e+01 3.65000000e-01 1.78000000e+00 0.00000000e+00 + 8.50000000e+01 2.30000000e-01 1.80000000e+00 0.00000000e+00 + 9.00000000e+01 9.00000000e-02 1.80000000e+00 0.00000000e+00 + 9.50000000e+01 -5.00000000e-02 1.78000000e+00 0.00000000e+00 + 1.00000000e+02 -1.85000000e-01 1.75000000e+00 0.00000000e+00 + 1.05000000e+02 -3.20000000e-01 1.70000000e+00 0.00000000e+00 + 1.10000000e+02 -4.50000000e-01 1.63500000e+00 0.00000000e+00 + 1.15000000e+02 -5.75000000e-01 1.55500000e+00 0.00000000e+00 + 1.20000000e+02 -6.70000000e-01 1.46500000e+00 0.00000000e+00 + 1.25000000e+02 -7.60000000e-01 1.35000000e+00 0.00000000e+00 + 1.30000000e+02 -8.50000000e-01 1.22500000e+00 0.00000000e+00 + 1.35000000e+02 -9.30000000e-01 1.08500000e+00 0.00000000e+00 + 1.40000000e+02 -9.80000000e-01 9.25000000e-01 0.00000000e+00 + 1.45000000e+02 -9.00000000e-01 7.55000000e-01 0.00000000e+00 + 1.50000000e+02 -7.70000000e-01 5.75000000e-01 0.00000000e+00 + 1.55000000e+02 -6.70000000e-01 4.20000000e-01 0.00000000e+00 + 1.60000000e+02 -6.35000000e-01 3.20000000e-01 0.00000000e+00 + 1.65000000e+02 -6.80000000e-01 2.30000000e-01 0.00000000e+00 + 1.70000000e+02 -8.50000000e-01 1.40000000e-01 0.00000000e+00 + 1.75000000e+02 -6.60000000e-01 5.50000000e-02 0.00000000e+00 + 1.80000000e+02 0.00000000e+00 2.50000000e-02 0.00000000e+00 + From 89ebcdf3ac97672fa9b96ee6980674cdb7edb715 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 11:16:27 -0600 Subject: [PATCH 06/11] Update execution until artifacts are set up --- examples/literate/A_simplyRunningOWENS.jl | 3 ++- examples/literate/C_customizablePreprocessing.jl | 1 + 2 files changed, 3 insertions(+), 1 deletion(-) diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index e28161a8..b7261939 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -51,6 +51,7 @@ simulated_time = 2.0 #seconds #md DLCs = ["7_1"] #"parked" #md DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] +Inp.ifw = false # set to false for automatic documentation until artifacts are set up OWENS.runDLC(DLCs,Inp,runpath; IEC_std="\"1-ED3\"", @@ -61,7 +62,7 @@ OWENS.runDLC(DLCs,Inp,runpath; Vdesign=11.0, grid_oversize=1.25, Vinf_range=[10.0],#LinRange(4,24,21), - regenWindFiles=true, + regenWindFiles=false, # set to false for automatic documentation until artifacts are set up delta_t_turbsim=0.05, simtime_turbsim=30.0, pathtoturbsim="$runpath/../../../OWENSOpenFASTWrappers.jl/deps/openfast/build/modules/turbsim/turbsim", diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index 4b4884c7..373e46fd 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -25,6 +25,7 @@ import OWENSOpenFASTWrappers runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") +Inp.ifw = false # set to false for automatic documentation until artifacts are set up nothing From 47cb8b3f236c35c4c2ce44fada1689015bf293f0 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 12:09:40 -0600 Subject: [PATCH 07/11] Expose OpenFASTWrappers path --- examples/literate/A_simplyRunningOWENS.jl | 6 ++---- examples/literate/B_detailedInputs.jl | 2 +- examples/literate/C_customizablePreprocessing.jl | 1 - 3 files changed, 3 insertions(+), 6 deletions(-) diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index b7261939..f5615c87 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -51,8 +51,6 @@ simulated_time = 2.0 #seconds #md DLCs = ["7_1"] #"parked" #md DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] -Inp.ifw = false # set to false for automatic documentation until artifacts are set up - OWENS.runDLC(DLCs,Inp,runpath; IEC_std="\"1-ED3\"", WindChar="\"A\"", @@ -62,10 +60,10 @@ OWENS.runDLC(DLCs,Inp,runpath; Vdesign=11.0, grid_oversize=1.25, Vinf_range=[10.0],#LinRange(4,24,21), - regenWindFiles=false, # set to false for automatic documentation until artifacts are set up + regenWindFiles=true, delta_t_turbsim=0.05, simtime_turbsim=30.0, - pathtoturbsim="$runpath/../../../OWENSOpenFASTWrappers.jl/deps/openfast/build/modules/turbsim/turbsim", + pathtoturbsim="$(OWENS.OWENSOpenFASTWrappers.OFWpath)/../deps/openfast/build/modules/turbsim/turbsim", runScript=OWENS.runOWENS) nothing \ No newline at end of file diff --git a/examples/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl index 1549c05c..aeec65a6 100644 --- a/examples/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -16,7 +16,7 @@ import OWENS import OWENSAero -# import PyPlot +#md import PyPlot runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index 373e46fd..4b4884c7 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -25,7 +25,6 @@ import OWENSOpenFASTWrappers runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") -Inp.ifw = false # set to false for automatic documentation until artifacts are set up nothing From d64a36d00708cfc6dbf055fc4ed0e08aae17f880 Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 13:55:10 -0600 Subject: [PATCH 08/11] update example C --- examples/literate/B_detailedInputs.jl | 4 + .../literate/C_customizablePreprocessing.jl | 385 ++++++++++++------ src/SetupTurbine.jl | 12 +- 3 files changed, 272 insertions(+), 129 deletions(-) diff --git a/examples/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl index aeec65a6..74a0b8c1 100644 --- a/examples/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -213,6 +213,10 @@ FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,ep epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) +if AD15On #TODO: move this into the run functions + OWENS.OWENSOpenFASTWrappers.endTurb() +end + nothing # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index 4b4884c7..a0d90ca6 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -18,11 +18,12 @@ import OWENSAero import QuadGK import FLOWMath import PyPlot -# PyPlot.pygui(true) +#md PyPlot.pygui(true) import OWENSOpenFASTWrappers runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] +#md runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") @@ -81,6 +82,7 @@ H = Blade_Height#1.02*R*2 #m shapeZ = collect(LinRange(0,H,Nslices+1)) shapeX = R.*(1.0.-4.0.*(shapeZ/H.-.5).^2) +shapeY = zeros(Nslices+1) stack_layers_bld = nothing @@ -93,6 +95,7 @@ strut_mountpointtop = 0.89 joint_type = 0 c_mount_ratio = 0.05 angularOffset = -pi/2 +custommesh = nothing if AModel=="AD" #TODO: unify flag AD15On=true #AD for AeroDyn, DMS for double multiple streamtube, AC for actuator cylinder else @@ -109,9 +112,12 @@ nothing # We do some intermediate calculations on the blade shape and angles Nstrutperbld = 2 #TODO: generalize and propogate - +strut_twr_mountpoint = [0.25,0.75] +strut_bld_mountpoint = [0.25,0.75] Nbld = B H = maximum(shapeZ) #m, +Htwr_blds = H +AD15hubR = 0.1 R = maximum(shapeX) #m, omega = RPM / 60 * 2 * pi tsr = omega*R/Vinf @@ -125,8 +131,8 @@ nothing ######################################### ### Set up mesh ######################################### -if meshtype == "ARCUS" #TODO, for all of these propogate the AeroDyn additional output requirements - mymesh,myort,myjoint = OWENS.create_arcus_mesh(;Htwr_base, +if meshtype == "ARCUS" && custommesh == nothing #TODO, for all of these propogate the AeroDyn additional output requirements + mymesh,myort,myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_arcus_mesh(;Htwr_base, Hbld = H, #blade height R, # m bade radius nblade = Nbld, @@ -136,10 +142,11 @@ if meshtype == "ARCUS" #TODO, for all of these propogate the AeroDyn additional c_mount_ratio, bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = shapeZ, + AD15_ccw = true, joint_type, #hinged about y axis cables_connected_to_blade_base, angularOffset) #Blade shape, magnitude is irrelevant, scaled based on height and radius above -elseif meshtype == "Darrieus" || meshtype == "H-VAWT" +elseif (meshtype == "Darrieus" || meshtype == "H-VAWT") && custommesh == nothing if meshtype == "Darrieus" connectBldTips2Twr = true @@ -148,29 +155,53 @@ elseif meshtype == "Darrieus" || meshtype == "H-VAWT" end mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = OWENS.create_mesh_struts(;Htwr_base, + Htwr_blds, Hbld = H, #blade height R, # m bade radius - AD15hubR=2.0, + AD15hubR, #TODO: hook up with AD15 file generation nblade = Nbld, ntelem, #tower elements nbelem, #blade elements nselem, - strut_twr_mountpoint = [strut_mountpointbot,strut_mountpointtop], # This puts struts at top and bottom - strut_bld_mountpoint = [strut_mountpointbot,strut_mountpointtop], # This puts struts at top and bottom + strut_twr_mountpoint, + strut_bld_mountpoint, bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above bshapez = shapeZ, - bshapey = zeros(nbelem+1), # but magnitude for this is relevant + bshapey = shapeY, # but magnitude for this is relevant angularOffset, #Blade shape, magnitude is irrelevant, scaled based on height and radius above AD15_ccw = true, verbosity=0, # 0 nothing, 1 basic, 2 lots: amount of printed information connectBldTips2Twr) +elseif custommesh != nothing + mymesh, myort, myjoint, AD15bldNdIdxRng, AD15bldElIdxRng = custommesh(;Htwr_base, + Htwr_blds, + Hbld = H, #blade height + R, # m bade radius + AD15hubR, #TODO: hook up with AD15 file generation + nblade = Nbld, + ntelem, #tower elements + nbelem, #blade elements + nselem, + strut_twr_mountpoint, + strut_bld_mountpoint, + bshapex = shapeX, #Blade shape, magnitude is irrelevant, scaled based on height and radius above + bshapez = shapeZ, + bshapey = shapeY, # but magnitude for this is relevant + angularOffset, #Blade shape, magnitude is irrelevant, scaled based on height and radius above + AD15_ccw = true, + verbosity=0, # 0 nothing, 1 basic, 2 lots: amount of printed information) + ) else #TODO unify with HAWT error("please choose a valid mesh type (Darrieus, H-VAWT, ARCUS)") end nTwrElem = Int(mymesh.meshSeg[1]) -if contains(NuMad_mat_xlscsv_file_bld,"34m") #TODO: this is really odd, - nTwrElem = Int(mymesh.meshSeg[1])+1 +try + if contains(NuMad_mat_xlscsv_file_bld,"34m") || meshtype == "ARCUS" #TODO: this is really odd, + nTwrElem = Int(mymesh.meshSeg[1])+1 + end +catch + nTwrElem = Int(mymesh.meshSeg[1]) end nothing @@ -178,14 +209,26 @@ nothing # Here is a way that you can visualize the nodal numbers of the mesh PyPlot.figure() -PyPlot.plot(mymesh.x,mymesh.z,"b-") - for myi = 1:length(mymesh.x) - PyPlot.text(mymesh.x[myi].+rand()/30,mymesh.z[myi].+rand()/30,"$myi",ha="center",va="center") - PyPlot.draw() - #sleep(0.1) - end +for icon = 1:length(mymesh.conn[:,1]) + idx1 = mymesh.conn[icon,1] + idx2 = mymesh.conn[icon,2] + PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"k.-") + PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center") + #md sleep(0.1) +end + +for ijoint = 1:length(myjoint[:,1]) + idx2 = Int(myjoint[ijoint,2]) + idx1 = Int(myjoint[ijoint,3]) + PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-") + PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center") + PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center") + #md sleep(0.1) +end PyPlot.xlabel("x") PyPlot.ylabel("y") +PyPlot.zlabel("z") + # This is where the sectional properties for the tower are either read in from the file, or are directly input and could be manuplated here in the script @@ -194,7 +237,7 @@ PyPlot.ylabel("y") ######################################### if !isnothing(NuMad_geom_xlscsv_file_twr) - numadIn_twr = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_twr) + numadIn_twr = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_twr;section=:tower) else n_web = 0 n_stack = 2 @@ -217,7 +260,7 @@ else numadIn_twr = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) end -#Add the full path +#md Add the full path for (i,airfoil) in enumerate(numadIn_twr.airfoil) numadIn_twr.airfoil[i] = "$path/airfoils/$airfoil" end @@ -244,7 +287,7 @@ nothing # For the blades, we repeat what was done for the tower, but also include some simple design options for scaling thicknesses, if !isnothing(NuMad_geom_xlscsv_file_bld) - numadIn_bld = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_bld) + numadIn_bld = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_bld;section=:blade) else n_web = 1 n_stack = 7 @@ -304,118 +347,160 @@ stiff_bld, mass_bld = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_bld,bld nothing # Similarly for the struts, we do what was done for the blades -if !isnothing(NuMad_geom_xlscsv_file_strut) - numadIn_strut = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut) -else - n_web = 1 - n_stack = 7 - n_segments = 12 - span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148] - airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"] - te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"] - twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] - chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0] - xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3] - aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2] - stack_mat_types = [8, 2, 4, 8, 8, 8, 4] - if isnothing(stack_layers_strut) - stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0] +numadIn_strut = Array{OWENS.NuMad, 1}(undef, Nstrutperbld) +strut_precompoutput = Array{Array{OWENS.OWENSPreComp.Output, 1},1}(undef, Nstrutperbld) +strut_precompinput = Array{Array{OWENS.OWENSPreComp.Input, 1},1}(undef, Nstrutperbld) +plyprops_strut = Array{OWENS.plyproperties, 1}(undef, Nstrutperbld) +lam_U_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld) +lam_L_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld) +lam_W_strut = Array{Array{OWENS.Composites.Laminate, 2}}(undef, Nstrutperbld) +sectionPropsArray_strut = Array{Array{OWENSFEA.SectionPropsArray, 1}}(undef, Nstrutperbld) +stiff_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld) +mass_strut = Array{Array{Array{Float64,2}, 1},1}(undef, Nstrutperbld) +for istrut = 1:Nstrutperbld + if !isnothing(NuMad_geom_xlscsv_file_strut) + if typeof(NuMad_geom_xlscsv_file_strut)==String + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut) + elseif typeof(NuMad_geom_xlscsv_file_strut) == OrderedCollections.OrderedDict{Symbol, Any} + if length(NuMad_geom_xlscsv_file_strut[:components][:struts])==1 + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut;section=:struts,subsection=1) + else + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut;section=:struts,subsection=istrut) + end + else + numadIn_strut[istrut] = OWENS.readNuMadGeomCSV(NuMad_geom_xlscsv_file_strut[istrut]) + end else - stack_layers = stack_layers_strut + n_web = 1 + n_stack = 7 + n_segments = 12 + span = [0.0, 6.607, 13.215, 19.822, 26.43, 33.037, 39.645, 46.252, 52.859, 59.467, 66.074, 72.682, 79.289, 85.896, 92.504, 99.111, 105.719, 112.326, 118.934, 125.541, 132.148] + airfoil = ["circular", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021", "NACA_0021"] + te_type = ["round", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp", "sharp"] + twist_d = [0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0] + chord = [10.0, 10.0, 9.0, 8.0, 8.0, 7.0, 7.0, 6.0, 6.0, 6.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0, 5.0] + xoffset = [0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3, 0.3] + aerocenter = [0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2, 0.2] + stack_mat_types = [8, 2, 4, 8, 8, 8, 4] + if isnothing(stack_layers_strut) + stack_layers = [30.0 2.0 15.0 25.0 25.0 2.0 13.0; 15.0 2.0 10.0 13.0 11.0 2.0 11.0; 10.0 1.0 8.0 10.0 10.0 2.0 10.0; 8.0 1.0 6.0 9.0 10.0 1.0 9.0; 7.0 1.0 5.0 8.0 9.0 1.0 7.0; 6.0 1.0 4.0 8.0 9.0 1.0 6.0; 6.0 1.0 4.0 8.0 8.0 1.0 5.0; 6.0 1.0 4.0 7.0 7.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 8.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 1.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 6.0 6.0 2.0 5.0; 7.0 1.0 3.0 7.0 8.0 3.0 5.0; 7.0 2.0 3.0 9.0 12.0 3.0 6.0; 10.0 3.0 4.0 11.0 15.0 3.0 6.0; 12.0 3.0 4.0 13.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 12.0 3.0 4.0 15.0 15.0 3.0 6.0; 10.0 1.0 4.0 10.0 12.0 1.0 5.0] + else + stack_layers = stack_layers_strut + end + segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0] + DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""] + skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])] + web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;] + web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;] + + numadIn_strut[istrut] = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) end - segments = [-1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0; -1.0 -0.95 -0.5 -0.3 -0.1 -0.095 0.0 0.095 0.1 0.3 0.5 0.95 1.0] - DPtypes = ["" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""; "" "" "" "" "" "" "" "" "" "" "" "" ""] - skin_seq = [Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2]); Seq([2, 5, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 1, 2]) Seq([2, 1, 2]) Seq([2, 3, 2]) Seq([2, 4, 2]) Seq([2, 4, 2]) Seq([2, 3, 2]) Seq([2, 5, 2])] - web_seq = [Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]); Seq([6, 7, 6]);;] - web_dp = [Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]); Seq([9, 3, 3, 9]);;] + for icol = 1:length(numadIn_strut[istrut].stack_layers[1,:]) + numadIn_strut[istrut].stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut[istrut].chord)) + end + #md numadIn_strut[istrut].chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut[istrut].chord)) - numadIn_strut = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) -end -for icol = 1:length(numadIn_strut.stack_layers[1,:]) - numadIn_strut.stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut.chord)) -end -numadIn_strut.chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut.chord)) + for (i,airfoil) in enumerate(numadIn_strut[istrut].airfoil) + numadIn_strut[istrut].airfoil[i] = "$path/airfoils/$airfoil" + end -for (i,airfoil) in enumerate(numadIn_strut.airfoil) - numadIn_strut.airfoil[i] = "$path/airfoils/$airfoil" -end + if !isnothing(NuMad_mat_xlscsv_file_strut) + plyprops_strut[istrut] = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_strut) + else + names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"] + plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)] + plyprops_strut[istrut] = OWENS.plyproperties(names,plies) + end -if !isnothing(NuMad_mat_xlscsv_file_strut) - plyprops_strut = OWENS.readNuMadMaterialsCSV(NuMad_mat_xlscsv_file_strut) -else - names = ["CLA_5500", "CBX_2400", "ETLX_2400", "Airex_C70_55", "EBX_2400_x10", "ETLX_2400_x10", "Airex_C70_55_x10", "CFP-baseline"] - plies = [Composites.Material{Float64}(9.824e10, 5.102e9, 4.274e9, 0.3, 1540.0, 8.75634139e8, 5.92949102e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(1.4931e10, 1.4931e10, 2.389e10, 0.3, 1530.0, 4.55053962e8, 4.55053962e8, 1.0e8, 1.0e8, 1.0e8, 0.0008100000000000001), Composites.Material{Float64}(2.0333e10, 9.305e9, 4.756e9, 0.3, 1900.0, 5.30896289e8, 5.30896289e8, 1.0e8, 1.0e8, 1.0e8, 0.00066), Composites.Material{Float64}(4.5e7, 4.5e7, 2.2e7, 0.2, 59.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 0.001), Composites.Material{Float64}(9.824e11, 5.102e10, 4.274e10, 0.3, 15300.0, 4.55053962e9, 4.55053962e9, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.4931e11, 1.4931e11, 2.389e11, 0.3, 19000.0, 5.30896289e9, 5.30896289e9, 1.0e8, 1.0e8, 1.0e8, 8.0e-5), Composites.Material{Float64}(2.03335e11, 9.3051e10, 4.756e10, 0.2, 590.0, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 1.0e8, 7.000000000000001e-5), Composites.Material{Float64}(1.576e11, 9.1e9, 3.3e9, 0.263, 1600.0, 2.236e9, 1.528e9, 1.0e8, 1.0e8, 1.0e8, 0.00066)] - plyprops_strut = OWENS.plyproperties(names,plies) -end + #md TODO: not straight struts + spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))] -#TODO: not straight struts -spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))] + if length(thickness_scale)==2 + yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_strut[istrut].span))) + elseif length(thickness_scale)==length(numadIn_strut[istrut].span) + yscale = thickness_scale + end -if length(thickness_scale)==2 - yscale = collect(LinRange(thickness_scale[1],thickness_scale[2],length(numadIn_strut.span))) -elseif length(thickness_scale)==length(numadIn_strut.span) - yscale = thickness_scale + strut_precompoutput[istrut],strut_precompinput[istrut],lam_U_strut[istrut],lam_L_strut[istrut],lam_W_strut[istrut] = OWENS.getOWENSPreCompOutput(numadIn_strut[istrut];yscale,plyprops = plyprops_strut[istrut]) + sectionPropsArray_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];precompinputs=strut_precompinput[istrut]) + stiff_strut[istrut], mass_strut[istrut] = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut[istrut],strut_precompoutput[istrut];GX=true) end -strut_precompoutput,strut_precompinput,lam_U_strut,lam_L_strut,lam_W_strut = OWENS.getOWENSPreCompOutput(numadIn_strut;yscale,plyprops = plyprops_strut) -sectionPropsArray_strut = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut,strut_precompoutput;precompinputs=strut_precompinput) -stiff_strut, mass_strut = OWENS.getSectPropsFromOWENSPreComp(spanpos,numadIn_strut,strut_precompoutput;GX=true) - nothing # Here we combine the section properties into an array matching the mesh elements bldssecprops = collect(Iterators.flatten(fill(sectionPropsArray_bld, Nbld))) -strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) +#md strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) if meshtype == "ARCUS" - cable_secprop = sectionPropsArray_twr[end] - Nremain = sum(Int,mymesh.meshSeg[Nbld+1+1:end]) #strut elements remain - sectionPropsArray = [fill(sectionPropsArray_twr[1],length(sectionPropsArray_twr));bldssecprops; fill(cable_secprop,Nremain)]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] + sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] - stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld))) # GXBeam sectional properties - stiff_cables = fill(stiff_twr[end],Nremain) - stiff_array = [stiff_twr; stiff_blds; stiff_cables] + stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld))) + stiff_array = [stiff_twr; stiff_blds]#; stiff_struts] mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld))) - mass_cables = fill(mass_twr[end],Nremain) - mass_array = [mass_twr; mass_blds; mass_cables] + mass_array = [mass_twr; mass_blds]#; mass_struts] + + for icable = 1:Nbld + sectionPropsArray = [sectionPropsArray; sectionPropsArray_strut[1]] + stiff_array = [stiff_array;stiff_strut[1]] + mass_array = [mass_array;mass_strut[1]] + end else - sectionPropsArray = [sectionPropsArray_twr; bldssecprops; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] - - stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld))) # GXBeam sectional properties - stiff_struts = collect(Iterators.flatten(fill(stiff_strut, Nstrutperbld*Nbld))) - stiff_array = [stiff_twr; stiff_blds; stiff_struts] + sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] + + stiff_blds = collect(Iterators.flatten(fill(stiff_bld, Nbld))) + stiff_array = [stiff_twr; stiff_blds]#; stiff_struts] mass_blds = collect(Iterators.flatten(fill(mass_bld, Nbld))) - mass_struts = collect(Iterators.flatten(fill(mass_strut, Nstrutperbld*Nbld))) - mass_array = [mass_twr; mass_blds; mass_struts] + mass_array = [mass_twr; mass_blds]#; mass_struts] + + for istrut = 1:Nstrutperbld + for ibld = 1:Nbld + global sectionPropsArray = [sectionPropsArray; sectionPropsArray_strut[istrut]] + global stiff_array = [stiff_array;stiff_strut[istrut]] + global mass_array = [mass_array;mass_strut[istrut]] + end + end end rotationalEffects = ones(mymesh.numEl) #TODO: non rotating tower, or rotating blades -myel = OWENSFEA.El(sectionPropsArray,myort.Length,myort.Psi_d,myort.Theta_d,myort.Twist_d,rotationalEffects) #store data in element object +if length(sectionPropsArray)Nbld # while the arms/struts are assumed to be straight and are oriented by the mesh angle BlSpn=collect(LinRange(0,bld_len[iADBody],blade_Nnodes[iADBody])) BlCrvAC=zeros(blade_Nnodes[iADBody]) - end - BlSwpAC=zeros(blade_Nnodes[iADBody]) - BlCrvAng=zeros(blade_Nnodes[iADBody]) - BlTwist=zeros(blade_Nnodes[iADBody]) - BlChord=blade_chords[iADBody] - BlAFID=collect(1:length(airfoil_filenames)) - OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID) + BlSwpAC=zeros(blade_Nnodes[iADBody]) + BlCrvAng=zeros(blade_Nnodes[iADBody]) + BlTwist=zeros(blade_Nnodes[iADBody]) + BlChord=blade_chords[iADBody] + BlAFID=collect((iADBody-1)*NumADStrutNds+1:iADBody*NumADStrutNds) + end + OWENSOpenFASTWrappers.writeADbladeFile(filename;NumBlNds=blade_Nnodes[iADBody],BlSpn,BlCrvAC,BlSwpAC,BlCrvAng,BlTwist,BlChord,BlAFID) end OWENSOpenFASTWrappers.writeOLAFfile(OLAF_filename;nNWPanel=200,nFWPanels=10) @@ -536,7 +675,7 @@ if AD15On hubPos=[[0,0,0.0]], hubAngle=[[0,0,0]], nacPos=[[0,0,0]], - adi_nstrut=[2], + adi_nstrut=[Nstrutperbld], adi_debug=0, isHAWT = false # true for HAWT, false for crossflow or VAWT ) diff --git a/src/SetupTurbine.jl b/src/SetupTurbine.jl index a8b4458f..b2723087 100644 --- a/src/SetupTurbine.jl +++ b/src/SetupTurbine.jl @@ -202,7 +202,7 @@ function setupOWENS(OWENSAero,path; numadIn_twr = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) end - #Add the full path + #md Add the full path for (i,airfoil) in enumerate(numadIn_twr.airfoil) numadIn_twr.airfoil[i] = "$path/airfoils/$airfoil" end @@ -414,7 +414,7 @@ function setupOWENS(OWENSAero,path; mass_array = [mass_array;fill(mass_strut[end][2],n_diff)] end - #store data in element object + #md store data in element object myel = OWENSFEA.El(sectionPropsArray,myort.Length,myort.Psi_d,myort.Theta_d,myort.Twist_d,rotationalEffects) system, assembly, sections = OWENS.owens_to_gx(mymesh,myort,myjoint,sectionPropsArray,stiff_array,mass_array) @@ -425,16 +425,16 @@ function setupOWENS(OWENSAero,path; ######################################### ### Set up aero forces ######################################### - # translate from blade span to blade height between the numad definition and the vertical slice positions - # First get the angles from the overall geometry npoints and go to the numad npoints + #md translate from blade span to blade height between the numad definition and the vertical slice positions + #md First get the angles from the overall geometry npoints and go to the numad npoints delta_xs = shapeX[2:end] - shapeX[1:end-1] delta_zs = shapeZ[2:end] - shapeZ[1:end-1] delta3D = atan.(delta_xs./delta_zs) delta3D_spl = safeakima(shapeZ[1:end-1]./maximum(shapeZ[1:end-1]), delta3D,LinRange(0,1,length(numadIn_bld.span)-1)) - # now convert the numad span to a height + #md now convert the numad span to a height bld_height_numad = cumsum(diff(numadIn_bld.span).*(1.0.-abs.(sin.(delta3D_spl)))) bld_height_numad_unit = bld_height_numad./maximum(bld_height_numad) - # now we can use it to access the numad data + #md now we can use it to access the numad data chord = safeakima(bld_height_numad_unit, numadIn_bld.chord,LinRange(bld_height_numad_unit[1],1,Nslices)) airfoils = fill("nothing",Nslices) From 1f3eb6650dc8418296e4471d277137169105395a Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 17:45:13 -0600 Subject: [PATCH 09/11] Change paths for auto docs --- examples/literate/A_simplyRunningOWENS.jl | 36 ++++++++-------- examples/literate/B_detailedInputs.jl | 4 +- .../literate/C_customizablePreprocessing.jl | 42 +++++++++---------- src/SetupTurbine.jl | 12 +++--- 4 files changed, 47 insertions(+), 47 deletions(-) diff --git a/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl index f5615c87..9c0a0dc4 100644 --- a/examples/literate/A_simplyRunningOWENS.jl +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -22,7 +22,7 @@ import OWENS runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] -#md runpath = path = splitdir(@__FILE__)[1] +##runpath = path = "/Users/kevmoor/Documents/coderepos/OWENS_Toolkit/OWENS.jl/examples/literate"#splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") @@ -33,23 +33,23 @@ OWENS.runOWENS(Inp,runpath) # One of these is the controller where a discon controller library can be coupled instead of the specified RPM control. simulated_time = 2.0 #seconds - DLCs = ["1_1"] #"normal" -#md DLCs = ["1_3"] #"normal" -#md DLCs = ["1_4"] #"normal" -#md DLCs = ["1_5"] #"normal" -#md DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" -#md DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" -#md DLCs = ["3_1"] #"startup" -#md DLCs = ["3_2"] #"startup" -#md DLCs = ["3_3"] #"startup" -#md DLCs = ["4_1"] #"shutdown" -#md DLCs = ["4_2"] #"shutdown" -#md DLCs = ["5_1"] #"emergencyshutdown" -#md DLCs = ["6_1"] #"parked" -#md DLCs = ["6_2"] #"parked_idle" -#md DLCs = ["6_4"] #"parked" -#md DLCs = ["7_1"] #"parked" -#md DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] +DLCs = ["1_1"] #"normal" +#### DLCs = ["1_3"] #"normal" +#### DLCs = ["1_4"] #"normal" +#### DLCs = ["1_5"] #"normal" +#### DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" +#### DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" +#### DLCs = ["3_1"] #"startup" +#### DLCs = ["3_2"] #"startup" +#### DLCs = ["3_3"] #"startup" +#### DLCs = ["4_1"] #"shutdown" +#### DLCs = ["4_2"] #"shutdown" +#### DLCs = ["5_1"] #"emergencyshutdown" +#### DLCs = ["6_1"] #"parked" +#### DLCs = ["6_2"] #"parked_idle" +#### DLCs = ["6_4"] #"parked" +#### DLCs = ["7_1"] #"parked" +#### DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] OWENS.runDLC(DLCs,Inp,runpath; IEC_std="\"1-ED3\"", diff --git a/examples/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl index 74a0b8c1..f289adf5 100644 --- a/examples/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -16,9 +16,9 @@ import OWENS import OWENSAero -#md import PyPlot +#### import PyPlot runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] - +## runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") nothing diff --git a/examples/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl index a0d90ca6..8a52629a 100644 --- a/examples/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -18,12 +18,12 @@ import OWENSAero import QuadGK import FLOWMath import PyPlot -#md PyPlot.pygui(true) +#### PyPlot.pygui(true) import OWENSOpenFASTWrappers runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] -#md runpath = path = splitdir(@__FILE__)[1] +## runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") @@ -214,7 +214,7 @@ for icon = 1:length(mymesh.conn[:,1]) idx2 = mymesh.conn[icon,2] PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"k.-") PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center") - #md sleep(0.1) + #### sleep(0.1) end for ijoint = 1:length(myjoint[:,1]) @@ -223,7 +223,7 @@ for ijoint = 1:length(myjoint[:,1]) PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-") PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center") PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center") - #md sleep(0.1) + #### sleep(0.1) end PyPlot.xlabel("x") PyPlot.ylabel("y") @@ -260,7 +260,7 @@ else numadIn_twr = NuMad(n_web,n_stack,n_segments,span,airfoil,te_type,twist_d,chord,xoffset,aerocenter,stack_mat_types,stack_layers,segments,DPtypes,skin_seq,web_seq,web_dp) end -#md Add the full path +#### Add the full path for (i,airfoil) in enumerate(numadIn_twr.airfoil) numadIn_twr.airfoil[i] = "$path/airfoils/$airfoil" end @@ -398,7 +398,7 @@ for istrut = 1:Nstrutperbld for icol = 1:length(numadIn_strut[istrut].stack_layers[1,:]) numadIn_strut[istrut].stack_layers[:,icol] .*= LinRange(stack_layers_scale[1],stack_layers_scale[2],length(numadIn_strut[istrut].chord)) end - #md numadIn_strut[istrut].chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut[istrut].chord)) + #### numadIn_strut[istrut].chord .*= LinRange(chord_scale[1],chord_scale[2],length(numadIn_strut[istrut].chord)) for (i,airfoil) in enumerate(numadIn_strut[istrut].airfoil) numadIn_strut[istrut].airfoil[i] = "$path/airfoils/$airfoil" @@ -412,7 +412,7 @@ for istrut = 1:Nstrutperbld plyprops_strut[istrut] = OWENS.plyproperties(names,plies) end - #md TODO: not straight struts + #### TODO: not straight struts spanpos = LinRange(0,1,nselem+1)#[0.0;cumsum(sqrt.(diff(mymesh.x[strut1start:strut1end]).^2 .+ diff(mymesh.z[strut1start:strut1end]).^2))] if length(thickness_scale)==2 @@ -430,7 +430,7 @@ nothing # Here we combine the section properties into an array matching the mesh elements bldssecprops = collect(Iterators.flatten(fill(sectionPropsArray_bld, Nbld))) -#md strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) +#### strutssecprops = collect(Iterators.flatten(fill(sectionPropsArray_strut, Nstrutperbld*Nbld))) if meshtype == "ARCUS" sectionPropsArray = [sectionPropsArray_twr; bldssecprops]#; strutssecprops]#;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str;sectionPropsArray_str] @@ -473,7 +473,7 @@ if length(sectionPropsArray) Date: Mon, 9 Sep 2024 18:43:09 -0600 Subject: [PATCH 10/11] Break up API reference to fit html size limits --- docs/make.jl | 7 +++++-- docs/src/reference/reference.md | 2 +- docs/src/reference/referenceAero.md | 14 ++++++++++++++ docs/src/reference/referenceFEA.md | 14 ++++++++++++++ docs/src/reference/referenceOpenFASTWrappers.md | 14 ++++++++++++++ docs/src/reference/referencePreComp.md | 14 ++++++++++++++ 6 files changed, 62 insertions(+), 3 deletions(-) create mode 100644 docs/src/reference/referenceAero.md create mode 100644 docs/src/reference/referenceFEA.md create mode 100644 docs/src/reference/referenceOpenFASTWrappers.md create mode 100644 docs/src/reference/referencePreComp.md diff --git a/docs/make.jl b/docs/make.jl index 1031a942..1ea44bf3 100644 --- a/docs/make.jl +++ b/docs/make.jl @@ -15,8 +15,11 @@ makedocs(; joinpath("examples", "C_customizablePreprocessing.md"), ], "Developer Guide" => "OWENS_Dev_Guide.md", - # "Frames of Reference" => "FramesOfReference.md", - "API Reference" => joinpath("reference", "reference.md"), + "OWENS Functions Reference" => joinpath("reference", "reference.md"), + "OWENSAero Functions Reference" => joinpath("reference", "referenceAero.md"), + "OWENSFEA Functions Reference" => joinpath("reference", "referenceFEA.md"), + "OWENSOpenFASTWrappers Functions Reference" => joinpath("reference", "referenceOpenFASTWrappers.md"), + "OWENSPreComp Functions Reference" => joinpath("reference", "referencePreComp.md"), "Legacy User Guide" => "legacyUserGuide.md", "Legacy VAWTGen Guide" => "VAWTGenUserGuide.md", ], diff --git a/docs/src/reference/reference.md b/docs/src/reference/reference.md index 1f417c72..fce53232 100644 --- a/docs/src/reference/reference.md +++ b/docs/src/reference/reference.md @@ -10,5 +10,5 @@ CurrentModule = OWENS ## Types and functions ```@autodocs -Modules = [OWENS,OWENS.OWENSAero,OWENS.OWENSFEA,OWENS.OWENSOpenFASTWrappers,OWENS.OWENSPreComp] +Modules = [OWENS] ``` \ No newline at end of file diff --git a/docs/src/reference/referenceAero.md b/docs/src/reference/referenceAero.md new file mode 100644 index 00000000..c35e00d9 --- /dev/null +++ b/docs/src/reference/referenceAero.md @@ -0,0 +1,14 @@ +```@meta +CurrentModule = OWENS +``` + +## Index + +```@index +``` + +## Types and functions + +```@autodocs +Modules = [OWENS.OWENSAero] +``` \ No newline at end of file diff --git a/docs/src/reference/referenceFEA.md b/docs/src/reference/referenceFEA.md new file mode 100644 index 00000000..b65cb1e5 --- /dev/null +++ b/docs/src/reference/referenceFEA.md @@ -0,0 +1,14 @@ +```@meta +CurrentModule = OWENS +``` + +## Index + +```@index +``` + +## Types and functions + +```@autodocs +Modules = [OWENS.OWENSFEA] +``` \ No newline at end of file diff --git a/docs/src/reference/referenceOpenFASTWrappers.md b/docs/src/reference/referenceOpenFASTWrappers.md new file mode 100644 index 00000000..4acb5d25 --- /dev/null +++ b/docs/src/reference/referenceOpenFASTWrappers.md @@ -0,0 +1,14 @@ +```@meta +CurrentModule = OWENS +``` + +## Index + +```@index +``` + +## Types and functions + +```@autodocs +Modules = [OWENS.OWENSOpenFASTWrappers] +``` \ No newline at end of file diff --git a/docs/src/reference/referencePreComp.md b/docs/src/reference/referencePreComp.md new file mode 100644 index 00000000..82f894b4 --- /dev/null +++ b/docs/src/reference/referencePreComp.md @@ -0,0 +1,14 @@ +```@meta +CurrentModule = OWENS +``` + +## Index + +```@index +``` + +## Types and functions + +```@autodocs +Modules = [OWENS.OWENSPreComp] +``` \ No newline at end of file From c3bb271507f4d7c4607ffd075abb3b29617a517a Mon Sep 17 00:00:00 2001 From: kevmoor Date: Mon, 9 Sep 2024 19:29:23 -0600 Subject: [PATCH 11/11] resolve next version number --- Project.toml | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/Project.toml b/Project.toml index 5c021409..d0e92815 100644 --- a/Project.toml +++ b/Project.toml @@ -1,7 +1,7 @@ name = "OWENS" uuid = "51d15398-4eaf-40f9-a029-79ae1c4a3867" authors = ["Kevin R. Moore and contributors"] -version = "1.0.3" +version = "1.0.2" [deps] Composites = "d0d699f6-c662-11e8-0fb1-1b30104ab829"