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" diff --git a/README.md b/README.md index ebabaece..53ea40de 100644 --- a/README.md +++ b/README.md @@ -1,12 +1,13 @@ # OWENS (Onshore/Offshore Wind/Water ENergy Simulator) [![](https://img.shields.io/badge/docs-stable-blue.svg)](https://sandialabs.github.io/OWENS.jl) +[![](https://img.shields.io/badge/docs-dev-blue.svg)](https://sandialabs.github.io/OWENS.jl/dev) ![](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 +54,7 @@ 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. 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/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/OWENS.code-profile b/docs/OWENS.code-profile new file mode 100644 index 00000000..f35fa1a5 --- /dev/null +++ b/docs/OWENS.code-profile @@ -0,0 +1 @@ +{"name":"owens_vscode_profile","settings":"{\"settings\":\"{\\n 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\ No newline at end of file diff --git a/docs/Project.toml b/docs/Project.toml index e3f07f6c..963ceafa 100644 --- a/docs/Project.toml +++ b/docs/Project.toml @@ -1,5 +1,6 @@ [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" 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..1ea44bf3 100644 --- a/docs/make.jl +++ b/docs/make.jl @@ -8,15 +8,18 @@ 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", - "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/setup/OWENS_Julia_VS.code-profile 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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 -# brew install gfortran - -# Update brew packages -brew upgrade - -# Install julia -brew install --cask julia - -# Install openfast coupled libraries !NOTE!: if you change the location of the compiled libraries, you may need to update the rpath variable, or recompile. -cd ../../../ -git clone --depth 1 https://github.com/OpenFAST/openfast.git -mkdir openfast/build -cd openfast/build -cmake -DBUILD_SHARED_LIBS=ON -DOPENMP=ON .. -make ifw_c_binding -make moordyn_c_binding -make hydrodyn_c_binding -make aerodyn_inflow_c_binding -make aerodyn_driver -make turbsim -cd ../../ - -# Install OWENS and non-registered dependencies as a regular user -julia -e 'using Pkg; Pkg.add(PackageSpec(url="git@github.com:kevmoor/GXBeam.jl.git"))' -julia -e 'using Pkg; Pkg.add(PackageSpec(url="https://github.com/byuflowlab/Composites.jl.git")); Pkg.add(PackageSpec(url="git@github.com:sandialabs/OWENSPreComp.jl.git")); Pkg.add(PackageSpec(url="git@github.com:sandialabs/OWENSOpenFASTWrappers.jl.git")); Pkg.add(PackageSpec(url="git@github.com:sandialabs/OWENSAero.jl.git")); Pkg.add(PackageSpec(url="git@github.com:sandialabs/OWENSFEA.jl.git")); Pkg.add(PackageSpec(url="git@github.com:sandialabs/OWENS.jl.git"))' - -# Add other registered packages for running the example scripts -julia -e 'using Pkg; Pkg.add("PyPlot");Pkg.add("Statistics");Pkg.add("DelimitedFiles");Pkg.add("Dierckx");Pkg.add("QuadGK");Pkg.add("FLOWMath");Pkg.add("HDF5")' - -# Run the example script -julia ExampleSNL5MW_turbulent.jl - -# Install Paraview -brew install --cask paraview - -# Install visual studio -brew install --cask visual-studio-code \ No newline at end of file diff --git a/docs/src/assets/OWENS_Processes.png b/docs/src/assets/OWENS_Processes.png new file mode 100644 index 00000000..e5814ad1 Binary files /dev/null and b/docs/src/assets/OWENS_Processes.png differ diff --git a/docs/src/index.md b/docs/src/index.md index a88b3bda..20faebd2 100644 --- a/docs/src/index.md +++ b/docs/src/index.md @@ -1,8 +1,11 @@ # OWENS (Onshore/Offshore Wind/Water ENergy Simulator) -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. +[![](https://img.shields.io/badge/docs-stable-blue.svg)](https://sandialabs.github.io/OWENS.jl) +![](https://github.com/sandialabs/OWENS.jl/workflows/CI/badge.svg) -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. +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. + +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. @@ -45,6 +48,8 @@ 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 @@ -53,7 +58,7 @@ 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 79% rename from docs/src/setup.md rename to docs/src/installation.md index 3d19323f..c587008a 100644 --- a/docs/src/setup.md +++ b/docs/src/installation.md @@ -1,26 +1,42 @@ # 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/ +<<<<<<< HEAD:docs/src/setup.md 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. +>>>>>>> 8e25223abc25ab4cbff6714daea56eaa9fd1a700:docs/src/installation.md ## Mac @@ -62,7 +78,11 @@ 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" # Environment Variables +<<<<<<< HEAD:docs/src/setup.md If you are using a proxy, be sure that the proxy variables are also declared/exported in your .bash_profile or .bashrc or the equivalent +======= +If you are using a proxy, be sure that the proxy variables are declared/exported in your .bash_profile or .bashrc or the equivalent +>>>>>>> 8e25223abc25ab4cbff6714daea56eaa9fd1a700:docs/src/installation.md http_proxy, https_proxy, HTTP_PROXY, HTTPS_PROXY, no_proxy, NO_PROXY git config --global http.proxy http://user:nopass@proxy.yourorg:number @@ -102,8 +122,12 @@ Additionally, if you find that your ssh is erroring when you try to install pack PubkeyAcceptedAlgorithms +ssh-ed25519 # Install Optional OpenFAST Dependices +<<<<<<< HEAD:docs/src/setup.md Note that this is optional as it is automatically done by julia in the OWENSOpenFASTWrappers.jl deps/build.jl. For Windows, please follow the OpenFAST Windows instructions on the openfast site for the branch referenced here. +======= +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. +>>>>>>> 8e25223abc25ab4cbff6714daea56eaa9fd1a700:docs/src/installation.md 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. @@ -297,7 +321,7 @@ 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 @@ -325,7 +349,7 @@ 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 @@ -334,13 +358,13 @@ 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 @@ -350,7 +374,7 @@ 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/A_simplyRunningOWENS.jl b/docs/src/literate/A_simplyRunningOWENS.jl deleted file mode 100644 index 285d13c9..00000000 --- a/docs/src/literate/A_simplyRunningOWENS.jl +++ /dev/null @@ -1,28 +0,0 @@ -# # [Simply Running OWENS](@id simple1) -# -# In this example, we show the first level of what is going on behind the precompiled binary -# Running julia directly with this as a starting point could make things like automating many runs in -# a way that is not compatible with the current interface, but your design design fits. -# -# OWENS is comprised of many building blocks. These series of examples progressively shows the internals -# of several of the key building blocks a new user might employ for their projects. Fundamentally, OWENS has been -# built to be as generalizable as possible. The lowest level of building blocks enable this, however, there are many -# common use cases for which helper functions have been developed, such as for meshing certain standard architectures -# and calculating and applying sectional properties to these architectures. The figure below summarizes this at a high -# level. -# TODO: yml file definition and inputs expanded -# -# ![](../assets/OWENS_Example_Figure_Building_Blocks.png) -# -#- -#md # !!! tip -#md # This example is also available as a Jupyter notebook todo: get link working: -#- - -import OWENS - -runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] - -Inp = OWENS.MasterInput("/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate/sampleOWENS.yml") - -OWENS.runOWENS(Inp,runpath) \ No newline at end of file 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_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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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 diff --git a/examples/SNL34m/SNL34mVAWTNormalOperation.jl b/examples/SNL34m/SNL34mVAWTNormalOperation.jl index 1dca2737..3c8ad510 100644 --- a/examples/SNL34m/SNL34mVAWTNormalOperation.jl +++ b/examples/SNL34m/SNL34mVAWTNormalOperation.jl @@ -160,6 +160,27 @@ mass_breakout_blds,mass_breakout_twr,system, assembly, sections,AD15bldNdIdxRng, angularOffset = pi/2, meshtype = turbineType) +PyPlot.figure() +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.plot3D([1,1],[1,1],[1,1],"k.-") + PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",ha="center",va="center") + # sleep(0.1) +end + +for ijoint = 1:length(myjoint[:,1]) + idx2 = Int(myjoint[ijoint,2]) + idx1 = Int(myjoint[ijoint,3]) + PyPlot.plot3D([mymesh.x[idx1],mymesh.x[idx2]],[mymesh.y[idx1],mymesh.y[idx2]],[mymesh.z[idx1],mymesh.z[idx2]],"r.-") + PyPlot.text3D(mymesh.x[idx1].+rand()/30,mymesh.y[idx1].+rand()/30,mymesh.z[idx1].+rand()/30,"$idx1",color="r",ha="center",va="center") + PyPlot.text3D(mymesh.x[idx2].+rand()/30,mymesh.y[idx2].+rand()/30,mymesh.z[idx2].+rand()/30,"$idx2",color="r",ha="center",va="center") + # sleep(0.1) +end +PyPlot.xlabel("x") +PyPlot.ylabel("y") +PyPlot.zlabel("z") RPM = 34.0 omega = RPM*2*pi/60 @@ -209,7 +230,7 @@ PyPlot.ylabel("Torque (kN-m)") PyPlot.xlim([0.0,25.0]) PyPlot.ylim([-25.0,150.0]) PyPlot.legend() -# PyPlot.savefig("$(path)/../figs/34m_fig3_6.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig3_6.pdf",transparent = true) ########################################## #### Power Plot @@ -227,7 +248,7 @@ PyPlot.xlim([0.0,25.0]) PyPlot.ylim([-100.0,600.0]) PyPlot.grid(linestyle="--") PyPlot.legend() -# PyPlot.savefig("$(path)/../figs/34m_fig3_7.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig3_7.pdf",transparent = true) ########################################## #### CP Plot @@ -254,7 +275,7 @@ PyPlot.ylabel("Power Coefficient") PyPlot.xlim([0,13]) PyPlot.ylim([0,0.8]) PyPlot.legend() -# PyPlot.savefig("$(path)/../figs/34m_fig3_8.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig3_8.pdf",transparent = true) ########################################## #### CT Plot @@ -268,7 +289,7 @@ PyPlot.ylabel("Thrust Coefficient") PyPlot.xlim([0,15]) PyPlot.ylim([0,0.9]) PyPlot.legend() -# PyPlot.savefig("$(path)/../figs/34m_figCT_34RPM.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_figCT_34RPM.pdf",transparent = true) ########################################## ############ AeroElastic ################# @@ -392,43 +413,43 @@ SNL34m_5_4_FlatwiseStress = DelimitedFiles.readdlm("$(path)/data/SAND-91-2228_Da # Plots PyPlot.figure() -PyPlot.plot(t.-offsetTime,flatwise_stress1[:,end-5]./1e6,"-",color=plot_cycle[1],label = "OWENS Blade 1") +PyPlot.plot(t.-offsetTime,flatwise_stress1[:,end-6]./1e6,"-",color=plot_cycle[1],label = "OWENS Blade 1") PyPlot.plot(SNL34m_5_4_FlatwiseStress[:,1].-0.8,SNL34m_5_4_FlatwiseStress[:,2],"k-",label = "Experimental") PyPlot.xlabel("Time (s)") PyPlot.ylabel("Flapwise Stress (MPa)") PyPlot.xlim([0,SNL34m_5_4_FlatwiseStress[end,1]]) # PyPlot.ylim([-60,0]) PyPlot.legend(loc = (0.06,1.0),ncol=2) -# PyPlot.savefig("$(path)/../figs/34m_fig5_4_NormalOperation_flapwise_Blade2Way.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig5_4_NormalOperation_flapwise_Blade2Way.pdf",transparent = true) println("here") exp_std_flap = Statistics.std(SNL34m_5_4_FlatwiseStress[:,2]) println("exp_std_flap $exp_std_flap") exp_mean_flap = Statistics.mean(SNL34m_5_4_FlatwiseStress[:,2]) println("exp_mean_flap $exp_mean_flap") -sim_std_flap = Statistics.std(flatwise_stress1[:,end-5]./1e6) +sim_std_flap = Statistics.std(flatwise_stress1[:,end-6]./1e6) println("sim_std_flap $sim_std_flap") -sim_mean_flap = Statistics.mean(flatwise_stress1[:,end-5]./1e6) +sim_mean_flap = Statistics.mean(flatwise_stress1[:,end-6]./1e6) println("sim_mean_flap $sim_mean_flap") SNL34m_5_4_LeadLagStress = DelimitedFiles.readdlm("$(path)/data/SAND-91-2228_Data/5.4AML.csv",',',skipstart = 1) PyPlot.figure() -PyPlot.plot(t.-offsetTime,lag_stress1[:,end-5]./1e6,"-",color=plot_cycle[1],label = "OWENS Blade 1") +PyPlot.plot(t.-offsetTime,lag_stress1[:,end-6]./1e6,"-",color=plot_cycle[1],label = "OWENS Blade 1") PyPlot.plot(SNL34m_5_4_LeadLagStress[:,1],SNL34m_5_4_LeadLagStress[:,2],"k-",label = "Experimental") PyPlot.xlabel("Time (s)") PyPlot.ylabel("Lead-Lag Stress (MPa)") PyPlot.xlim([0,SNL34m_5_4_LeadLagStress[end,1]]) PyPlot.legend(loc = (0.06,1.0),ncol=2) -# PyPlot.savefig("$(path)/../figs/34m_fig5_4_NormalOperation_LeadLag_Blade2Way.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig5_4_NormalOperation_LeadLag_Blade2Way.pdf",transparent = true) exp_std_lag = Statistics.std(SNL34m_5_4_LeadLagStress[:,2]) println("exp_std_lag $exp_std_lag") exp_mean_lag = Statistics.mean(SNL34m_5_4_LeadLagStress[:,2]) println("exp_mean_lag $exp_mean_lag") -sim_std_lag = Statistics.std(lag_stress1[:,end-5]./1e6) +sim_std_lag = Statistics.std(lag_stress1[:,end-6]./1e6) println("sim_std_lag $sim_std_lag") -sim_mean_lag = Statistics.mean(lag_stress1[:,end-5]./1e6) +sim_mean_lag = Statistics.mean(lag_stress1[:,end-6]./1e6) println("sim_mean_lag $sim_mean_lag") ########################################## @@ -447,7 +468,7 @@ PyPlot.xlabel("Time (s)") PyPlot.xlim([0,100]) PyPlot.ylabel("Torque (kN-m)") PyPlot.legend()#loc = (0.06,1.0),ncol=2) -# PyPlot.savefig("$(path)/../figs/34m_fig5_32Way.pdf",transparent = true) +PyPlot.savefig("$(path)/figs/34m_fig5_32Way.pdf",transparent = true) # #Extract and Plot Frequency - Amplitude @@ -583,4 +604,4 @@ end azi=aziHist#./aziHist*1e-6 saveName = "$path/vtk/SNL34mVAWTNormalOperation" -OWENS.OWENSFEA_VTK(saveName,t,uHist,system,assembly,sections;scaling=1,azi,userPointNames,userPointData) +# OWENS.OWENSFEA_VTK(saveName,t,uHist,system,assembly,sections;scaling=1,azi,userPointNames,userPointData) diff --git a/examples/SNL34m/SNL34m_Inputs.yml b/examples/SNL34m/SNL34m_Inputs.yml index 925b210a..fcac4630 100644 --- a/examples/SNL34m/SNL34m_Inputs.yml +++ b/examples/SNL34m/SNL34m_Inputs.yml @@ -23,19 +23,19 @@ turbulentInflow: controlParameters: controlStrategy: constantRPM # TODO: incorporate the others RPM: 34.0 #RPM - numTS: 5000 # + numTS: 1000 # delta_t: 0.05 # s 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" structuralParameters: - structuralModel: GX #GX, TNB, ROM + structuralModel: ROM #GX, TNB, ROM nonlinear: false #TODO: propogate ntelem: 20 #tower elements in each nbelem: 60 #blade elements in each 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/examples/literate/A_simplyRunningOWENS.jl b/examples/literate/A_simplyRunningOWENS.jl new file mode 100644 index 00000000..9c0a0dc4 --- /dev/null +++ b/examples/literate/A_simplyRunningOWENS.jl @@ -0,0 +1,69 @@ +# # [Simply Running OWENS](@id simple1) +# +# In this example, we show the first level of what is going on behind the precompiled binary +# Running julia directly with this as a starting point could make things like automating many runs in +# a way that is not compatible with the current interface, but your design design fits. +# +# OWENS is comprised of many building blocks. These series of examples progressively shows the internals +# of several of the key building blocks a new user might employ for their projects. Fundamentally, OWENS has been +# built to be as generalizable as possible. The lowest level of building blocks enable this, however, there are many +# common use cases for which helper functions have been developed, such as for meshing certain standard architectures +# and calculating and applying sectional properties to these architectures. The figure below summarizes this at a high +# level. +# TODO: yml file definition and inputs expanded +# +# ![](../assets/OWENS_Example_Figure_Building_Blocks.png) +# +#- +#md # !!! tip +#md # This example is also available as a Jupyter notebook todo: get link working: +#- + +import OWENS + +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] +##runpath = path = "/Users/kevmoor/Documents/coderepos/OWENS_Toolkit/OWENS.jl/examples/literate"#splitdir(@__FILE__)[1] + +Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") + +OWENS.runOWENS(Inp,runpath) + +# Here is an example of using the same model against the automated DLC run script. +# Note that for a setup cutom to a specific design, you'll want to go to the B level to get all of the detailed inputs correct +# One of these is the controller where a discon controller library can be coupled instead of the specified RPM control. + +simulated_time = 2.0 #seconds +DLCs = ["1_1"] #"normal" +#### DLCs = ["1_3"] #"normal" +#### DLCs = ["1_4"] #"normal" +#### DLCs = ["1_5"] #"normal" +#### DLCs = ["2_1"] #"freewheelatNormalOperatingRPM" +#### DLCs = ["2_3"] #"freewheelatNormalOperatingRPM" +#### DLCs = ["3_1"] #"startup" +#### DLCs = ["3_2"] #"startup" +#### DLCs = ["3_3"] #"startup" +#### DLCs = ["4_1"] #"shutdown" +#### DLCs = ["4_2"] #"shutdown" +#### DLCs = ["5_1"] #"emergencyshutdown" +#### DLCs = ["6_1"] #"parked" +#### DLCs = ["6_2"] #"parked_idle" +#### DLCs = ["6_4"] #"parked" +#### DLCs = ["7_1"] #"parked" +#### DLCs = ["2_3","3_1","3_2","3_3","4_1","4_2","5_1"] + +OWENS.runDLC(DLCs,Inp,runpath; + IEC_std="\"1-ED3\"", + WindChar="\"A\"", + WindClass=1, + NumGrid_Z=38, + NumGrid_Y=26, + Vdesign=11.0, + grid_oversize=1.25, + Vinf_range=[10.0],#LinRange(4,24,21), + regenWindFiles=true, + delta_t_turbsim=0.05, + simtime_turbsim=30.0, + pathtoturbsim="$(OWENS.OWENSOpenFASTWrappers.OFWpath)/../deps/openfast/build/modules/turbsim/turbsim", + runScript=OWENS.runOWENS) + +nothing \ No newline at end of file diff --git a/docs/src/literate/B_detailedInputs.jl b/examples/literate/B_detailedInputs.jl similarity index 96% rename from docs/src/literate/B_detailedInputs.jl rename to examples/literate/B_detailedInputs.jl index 2da08541..f289adf5 100644 --- a/docs/src/literate/B_detailedInputs.jl +++ b/examples/literate/B_detailedInputs.jl @@ -16,10 +16,9 @@ import OWENS import OWENSAero -# import PyPlot - -path = runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] - +#### 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("$runpath/sampleOWENS.yml") nothing @@ -111,6 +110,8 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A NuMad_geom_xlscsv_file_strut, NuMad_mat_xlscsv_file_strut, Htwr_base=towerHeight, + strut_twr_mountpoint = [0.25,0.75], + strut_bld_mountpoint = [0.25,0.75], ntelem, nbelem, ncelem, @@ -212,6 +213,10 @@ FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,ep epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) +if AD15On #TODO: move this into the run functions + OWENS.OWENSOpenFASTWrappers.endTurb() +end + nothing # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the diff --git a/docs/src/literate/C_customizablePreprocessing.jl b/examples/literate/C_customizablePreprocessing.jl similarity index 63% rename from docs/src/literate/C_customizablePreprocessing.jl rename to examples/literate/C_customizablePreprocessing.jl index acfee8aa..8a52629a 100644 --- a/docs/src/literate/C_customizablePreprocessing.jl +++ b/examples/literate/C_customizablePreprocessing.jl @@ -18,11 +18,12 @@ import OWENSAero import QuadGK import FLOWMath import PyPlot -# PyPlot.pygui(true) +#### PyPlot.pygui(true) import OWENSOpenFASTWrappers -path = runpath = "/home/runner/work/OWENS.jl/OWENS.jl/docs/src/literate" #splitdir(@__FILE__)[1] +runpath = path = "/home/runner/work/OWENS.jl/OWENS.jl/examples/literate" # to run locally, change to splitdir(@__FILE__)[1] +## runpath = path = splitdir(@__FILE__)[1] Inp = OWENS.MasterInput("$runpath/sampleOWENS.yml") @@ -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") + #### 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") + #### 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 +#### 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 + #### 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 + #### 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))) +#### 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/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/docs/src/literate/airfoils/NACA_0018_AllRe.dat b/examples/literate/airfoils/NACA_0018.dat similarity index 99% rename from docs/src/literate/airfoils/NACA_0018_AllRe.dat rename to examples/literate/airfoils/NACA_0018.dat index e4b94c5a..91a33ff6 100644 --- a/docs/src/literate/airfoils/NACA_0018_AllRe.dat +++ b/examples/literate/airfoils/NACA_0018.dat @@ -6,7 +6,7 @@ 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. +@"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. ! ------------------------------------------------------------------------------ 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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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 90% rename from docs/src/literate/sampleOWENS.yml rename to examples/literate/sampleOWENS.yml index 9e646677..551484c5 100644 --- a/docs/src/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 @@ -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 diff --git a/src/PostProcessing.jl b/src/PostProcessing.jl index 2d043892..74b9edad 100644 --- a/src/PostProcessing.jl +++ b/src/PostProcessing.jl @@ -314,7 +314,7 @@ end function calcSF(stress,SF_ult,SF_buck,lencomposites_span,plyprops, precompinput,precompoutput,lam_in,eps_x,eps_z,eps_y,kappa_x, - kappa_y,kappa_z,numadIn;failmethod = "maxstress",CLT=false,upper=true,layer=-1) + kappa_y,kappa_z,numadIn;failmethod = "maxstress",CLT=false,upper=true,layer=-1,calculate_fatigue=true) topstrainout = zeros(length(eps_x[1,:,1]),lencomposites_span,length(lam_in[1,:]),9) # time, span, lam, x,y, Assumes you use zero plies for sections that aren't used damage = zeros(lencomposites_span,length(lam_in[1,:])) #span length, with number of laminates, with number of plies NOTE: this assumes the number of plies is constant across all span and laminate locations @@ -441,28 +441,30 @@ function calcSF(stress,SF_ult,SF_buck,lencomposites_span,plyprops, end # Miner's Damage - damage_layers = zeros(length(lam.nply)) - for ilayer = 1:length(lam.nply) - #TODO: multiple mean ranges and goodman correction, also non-principal stress - stressForFatigue = stress_eachlayer[:,ilayer,1] - Ncycles,meanIntervals,rangeIntervals,_ = rainflow(stressForFatigue;nbins_range=20,nbins_mean=1,m=3,Teq=1) - imean = 1 - cyclesatStressRanges = Ncycles[imean,:] - stress_levels = (rangeIntervals[1:end-1] .+ rangeIntervals[2:end])./2 #from intervals to mean between the interval - - SN_stressMpa1 = SN_stressMpa[ilayer] - Log_SN_cycles2Fail1 = Log_SN_cycles2Fail[ilayer] - - if Log_SN_cycles2Fail1[2]>Log_SN_cycles2Fail1[1] - reverse!(SN_stressMpa1) - reverse!(Log_SN_cycles2Fail1) - end + if calculate_fatigue + damage_layers = zeros(length(lam.nply)) + for ilayer = 1:length(lam.nply) + #TODO: multiple mean ranges and goodman correction, also non-principal stress + stressForFatigue = stress_eachlayer[:,ilayer,1] + Ncycles,meanIntervals,rangeIntervals,_ = rainflow(stressForFatigue;nbins_range=20,nbins_mean=1,m=3,Teq=1) + imean = 1 + cyclesatStressRanges = Ncycles[imean,:] + stress_levels = (rangeIntervals[1:end-1] .+ rangeIntervals[2:end])./2 #from intervals to mean between the interval + + SN_stressMpa1 = SN_stressMpa[ilayer] + Log_SN_cycles2Fail1 = Log_SN_cycles2Fail[ilayer] + + if Log_SN_cycles2Fail1[2]>Log_SN_cycles2Fail1[1] + reverse!(SN_stressMpa1) + reverse!(Log_SN_cycles2Fail1) + end - logcycles2fail = safeakima(SN_stressMpa1.*1e6,Log_SN_cycles2Fail1,stress_levels) - cycles2fail = 10.0 .^ logcycles2fail - damage_layers[ilayer] = sum(cyclesatStressRanges./cycles2fail) + logcycles2fail = safeakima(SN_stressMpa1.*1e6,Log_SN_cycles2Fail1,stress_levels) + cycles2fail = 10.0 .^ logcycles2fail + damage_layers[ilayer] = sum(cyclesatStressRanges./cycles2fail) + end + damage[i_station,j_lam] = maximum(damage_layers) end - damage[i_station,j_lam] = maximum(damage_layers) end end return topstrainout,damage @@ -625,7 +627,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l 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,throwawayTimeSteps=1,delta_t=0.001,AD15bldNdIdxRng=nothing,AD15bldElIdxRng=nothing, - strut_precompoutput=nothing,strut_precompinput=nothing,plyprops_strut=nothing,numadIn_strut=nothing,lam_U_strut=nothing,lam_L_strut=nothing) + strut_precompoutput=nothing,strut_precompinput=nothing,plyprops_strut=nothing,numadIn_strut=nothing,lam_U_strut=nothing,lam_L_strut=nothing,calculate_fatigue=true) # Linearly Superimpose the Strains epsilon_x_hist = epsilon_x_hist_ps#copy(epsilon_x_hist_ps).*0.0 @@ -797,7 +799,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_blade_U,topDamage_blade_U = calcSF(stress_U,SF_ult_U,SF_buck_U,length(bld_precompinput),plyprops_bld, bld_precompinput,bld_precompoutput,lam_U_bld,eps_x_bld,eps_z_bld,eps_y_bld,kappa_x_bld, - kappa_y_bld,kappa_z_bld,numadIn_bld;failmethod = "maxstress",upper=true) + kappa_y_bld,kappa_z_bld,numadIn_bld;failmethod = "maxstress",upper=true,calculate_fatigue) if verbosity>0 println("Composite Ultimate and Buckling Safety Factors") @@ -816,7 +818,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_blade_L,topDamage_blade_L = calcSF(stress_L,SF_ult_L,SF_buck_L,length(bld_precompinput),plyprops_bld, bld_precompinput,bld_precompoutput,lam_L_bld,eps_x_bld,eps_z_bld,eps_y_bld,kappa_x_bld, - kappa_y_bld,kappa_z_bld,numadIn_bld;failmethod = "maxstress",upper=false) + kappa_y_bld,kappa_z_bld,numadIn_bld;failmethod = "maxstress",upper=false,calculate_fatigue) if verbosity>0 println("\n\nLOWER BLADE SURFACE") @@ -838,7 +840,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_strut_U,topDamage_strut_U = calcSF(stress_U_strut,SF_ult_U_strut,SF_buck_U_strut,length(strut_precompinput),plyprops_strut, strut_precompinput,strut_precompoutput,lam_U_strut,eps_x_strut,eps_z_strut,eps_y_strut,kappa_x_strut, - kappa_y_strut,kappa_z_strut,numadIn_strut;failmethod = "maxstress",upper=true) + kappa_y_strut,kappa_z_strut,numadIn_strut;failmethod = "maxstress",upper=true,calculate_fatigue) if verbosity>0 println("Composite Ultimate and Buckling Safety Factors") @@ -857,7 +859,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_strut_L,topDamage_strut_L = calcSF(stress_L_strut,SF_ult_L_strut,SF_buck_L_strut,length(strut_precompinput),plyprops_strut, strut_precompinput,strut_precompoutput,lam_L_strut,eps_x_strut,eps_z_strut,eps_y_strut,kappa_x_strut, - kappa_y_strut,kappa_z_strut,numadIn_strut;failmethod = "maxstress",upper=false) + kappa_y_strut,kappa_z_strut,numadIn_strut;failmethod = "maxstress",upper=false,calculate_fatigue) if verbosity>0 println("\n\nLOWER STRUT SURFACE") @@ -888,7 +890,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_tower_U,topDamage_tower_U = calcSF(stress_TU,SF_ult_TU,SF_buck_TU,length(twr_precompinput),plyprops_twr, twr_precompinput,twr_precompoutput,lam_U_twr,eps_x_twr,eps_z_twr,eps_y_twr,kappa_x_twr, - kappa_y_twr,kappa_z_twr,numadIn_twr;failmethod = "maxstress",upper=true) + kappa_y_twr,kappa_z_twr,numadIn_twr;failmethod = "maxstress",upper=true,calculate_fatigue) println("\n\nUPPER TOWER") printsf_twr(verbosity,lam_U_twr,SF_ult_TU,SF_buck_TU,length(twr_precompinput),Twr_LE_U_idx,topDamage_tower_U,delta_t,total_t) @@ -899,7 +901,7 @@ function extractSF(bld_precompinput,bld_precompoutput,plyprops_bld,numadIn_bld,l topstrainout_tower_L,topDamage_tower_L = calcSF(stress_TL,SF_ult_TL,SF_buck_TL,length(twr_precompinput),plyprops_twr, twr_precompinput,twr_precompoutput,lam_U_twr,eps_x_twr,eps_z_twr,eps_y_twr,kappa_x_twr, - kappa_y_twr,kappa_z_twr,numadIn_twr;failmethod = "maxstress",upper=false) + kappa_y_twr,kappa_z_twr,numadIn_twr;failmethod = "maxstress",upper=false,calculate_fatigue) println("\n\nLower TOWER") printsf_twr(verbosity,lam_L_twr,SF_ult_TL,SF_buck_TL,length(twr_precompinput),Twr_LE_L_idx,topDamage_tower_L,delta_t,total_t) diff --git a/src/SetupTurbine.jl b/src/SetupTurbine.jl index a8b4458f..93a9bf48 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 + #### 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 + #### 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 + #### 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 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 + #### 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 + #### 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) diff --git a/src/topRunDLC.jl b/src/topRunDLC.jl index 3c2dc435..ba165e6c 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: $controlStrategy") + inputs = OWENS.Inputs(;analysisType = structuralModel, - tocp = [0.0,100000.1], - Omegaocp = [RPM,RPM] ./ 60, + tocp, + Omegaocp, tocp_Vinf = [0.0,100000.1], Vinfocp = [Vinf,Vinf], numTS, delta_t, AD15On, - aeroLoadsOn = 2) + aeroLoadsOn = 2, + turbineStartup, + generatorOn, + useGeneratorFunction, + OmegaInit = Omegaocp[1]) nothing @@ -303,7 +356,8 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A joint = myjoint, platformTurbineConnectionNodeNumber = 1, pBC, - nlOn = true, + nlOn = false, + gravityOn = true, numNodes = mymesh.numNodes, RayleighAlpha = 0.05, RayleighBeta = 0.05, @@ -317,17 +371,25 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A println("Running Unsteady") t, aziHist,OmegaHist,OmegaDotHist,gbHist,gbDotHist,gbDotDotHist,FReactionHist, FTwrBsHist,genTorque,genPower,torqueDriveShaft,uHist,uHist_prp,epsilon_x_hist,epsilon_y_hist, - epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist = OWENS.Unsteady_Land(inputs;system,assembly, + epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist,FPtfmHist,FHydroHist,FMooringHist, + topFexternal_hist,rbDataHist = OWENS.Unsteady_Land(inputs;system,assembly, topModel=feamodel,topMesh=mymesh,topEl=myel,aero=aeroForces,deformAero) + if AModel=="AD" + OWENSOpenFASTWrappers.endTurb() + end + nothing # Like described above, we can output vtk files viewable in paraview. Here it is done for each time step and shows the # deformations. Additionaly, there is a method to input custom values and have them show up on the vtk surface mesh # for example, strain, or reaction force, etc. This is described in more detail in the api reference for the function and: TODO - println("Saving VTK time domain files") - OWENS.OWENSFEA_VTK("$path/vtk/SNLARCUS5MW_timedomain_TNBnltrue",t,uHist,system,assembly,sections;scaling=1,azi=aziHist) + azi=aziHist#./aziHist*1e-6 + saveName = "$path/vtk/SNL5MW" + OWENS.OWENSVTK(saveName,t,uHist,system,assembly,sections,aziHist,mymesh,myel, + epsilon_x_hist,epsilon_y_hist,epsilon_z_hist,kappa_x_hist,kappa_y_hist,kappa_z_hist, + FReactionHist,topFexternal_hist) nothing @@ -340,18 +402,62 @@ mass_breakout_blds,mass_breakout_twr,system,assembly,sections,AD15bldNdIdxRng, A massOwens,stress_U,SF_ult_U,SF_buck_U,stress_L,SF_ult_L,SF_buck_L,stress_TU,SF_ult_TU, SF_buck_TU,stress_TL,SF_ult_TL,SF_buck_TL,topstrainout_blade_U,topstrainout_blade_L, - topstrainout_tower_U,topstrainout_tower_LtopDamage_blade_U, + topstrainout_tower_U,topstrainout_tower_L,topDamage_blade_U, topDamage_blade_L,topDamage_tower_U,topDamage_tower_L = OWENS.extractSF(bld_precompinput, bld_precompoutput,plyprops_bld,numadIn_bld,lam_U_bld,lam_L_bld, twr_precompinput,twr_precompoutput,plyprops_twr,numadIn_twr,lam_U_twr,lam_L_twr, - mymesh,myel,myort,Nbld,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, + mymesh,myel,myort,B,epsilon_x_hist,kappa_y_hist,kappa_z_hist,epsilon_z_hist, kappa_x_hist,epsilon_y_hist;verbosity, #Verbosity 0:no printing, 1: summary, 2: summary and spanwise worst safety factor # epsilon_x_hist_1,kappa_y_hist_1,kappa_z_hist_1,epsilon_z_hist_1,kappa_x_hist_1,epsilon_y_hist_1, LE_U_idx=1,TE_U_idx=6,SparCapU_idx=3,ForePanelU_idx=2,AftPanelU_idx=5, LE_L_idx=1,TE_L_idx=6,SparCapL_idx=3,ForePanelL_idx=2,AftPanelL_idx=5, Twr_LE_U_idx=1,Twr_LE_L_idx=1, AD15bldNdIdxRng,AD15bldElIdxRng,strut_precompoutput=nothing) #TODO: add in ability to have material safety factors and load safety factors - return [1.0,2.0,3.0] + dataDumpFilename = "$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