From 4d534b3385a4dc33e674c17ac137b84e498f5158 Mon Sep 17 00:00:00 2001 From: Prashanth <61168530+askprash@users.noreply.github.com> Date: Thu, 14 Dec 2023 19:51:51 -0500 Subject: [PATCH] Clean up duplicate/ old files (#6) * del old airtable * del old blax * air --> airfoil_data + add additional airfoils --- docs/src/aero/drag.md | 2 +- src/aero/aero.jl | 5 +- src/aero/airfun.jl | 2 +- src/aero/airtable.jl | 101 +- src/aero/airtable2.jl | 120 -- src/aero/blax.jl | 499 ++++--- src/aero/blax2.jl | 652 --------- src/aero/blsys.jl | 2 +- src/aero/fusebl.jl | 4 +- src/{air => airfoil_data}/C.air | 0 src/airfoil_data/Cl.air | 1966 ++++++++++++++++++++++++++++ src/airfoil_data/E.air | 2183 +++++++++++++++++++++++++++++++ src/airfoil_data/README | 14 + test/unit_test_aero.jl | 2 +- 14 files changed, 4554 insertions(+), 998 deletions(-) delete mode 100644 src/aero/airtable2.jl delete mode 100644 src/aero/blax2.jl rename src/{air => airfoil_data}/C.air (100%) create mode 100644 src/airfoil_data/Cl.air create mode 100644 src/airfoil_data/E.air create mode 100644 src/airfoil_data/README diff --git a/docs/src/aero/drag.md b/docs/src/aero/drag.md index 4c549de0..2332466e 100644 --- a/docs/src/aero/drag.md +++ b/docs/src/aero/drag.md @@ -43,7 +43,7 @@ aerodynamics.blsys(simi,lami,wake,direct, Mach, uinv, cfm, cfm_thm, cfm_dsm, cfm_uem, dim, dim_thm, dim_dsm, dim_uem) -aerodynamics.blax2(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) +aerodynamics.blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) aerodynamics.blvar(simi,lami,wake, Reyn,Mach, fexcr, x, θ ,δs ,ue ) diff --git a/src/aero/aero.jl b/src/aero/aero.jl index 667f729d..03571a14 100644 --- a/src/aero/aero.jl +++ b/src/aero/aero.jl @@ -35,11 +35,11 @@ jdim::Int = 360 # Aerofoil calculations include("airfoil.jl") -include("airtable2.jl") +include("airtable.jl") include("airfun.jl") __abs_path_prefix__ = dirname(@__DIR__) -airfoil_data = joinpath(__abs_path_prefix__,"air/C.air") +airfoil_data = joinpath(__abs_path_prefix__,"airfoil_data/C.air") airsection = airtable(airfoil_data); @@ -53,7 +53,6 @@ include("wingsc.jl") include("fusebl.jl") include("axisol.jl") include("blax.jl") -include("blax2.jl") include("blsys.jl") # Trefftz plane CDi calcs diff --git a/src/aero/airfun.jl b/src/aero/airfun.jl index 68871b2f..8fbd7a91 100644 --- a/src/aero/airfun.jl +++ b/src/aero/airfun.jl @@ -3,7 +3,7 @@ export airfun """ airfun(cl, τ, Mach, air::airfoil) -Looks up airfoil performance data at specified conditions, as precomputed and found in `./src/air/C.air`. +Looks up airfoil performance data at specified conditions, as precomputed and found in `./src/airfoil_data/`. !!! details "🔃 Inputs and Outputs" **Inputs:** diff --git a/src/aero/airtable.jl b/src/aero/airtable.jl index 69f13b98..ff5fc98d 100644 --- a/src/aero/airtable.jl +++ b/src/aero/airtable.jl @@ -1,22 +1,31 @@ -using Dierckx - """ -Reads airfoil file and outputs a matrix and spline objects + airtable(fname) + +Reads airfoil file and outputs the matrix and splines as an `airfoil`. + +The airfoil data is stored as a function of three variables, typically +Mach number ``\\mathrm{Ma}``, lift coefficient ``c_l``, and thickness to chord ratio ``\\tau``. + + cdf(Ma, cl, τ), cdp(Ma, cl, τ), cm(Ma, cl, τ) + +!!! details "🔃 Inputs and Outputs" + **Inputs:** + - `fname::String`: Path to file. -!!! compat "Future Changes" - Deprecated by faster [`airtable`](@ref) in `airtable2.jl`. Will be removed in a future revision. + **Outputs:** + - `airf::TASOPT.aerodynamics.airfoil`: struct with airfoil performance characteristics. """ function airtable(fname) - # Read file - f = open(fname) +# Read airfoil data +f = open(fname) nAMa::Int, nAcl::Int, nAτ::Int, nAfun::Int = [parse(Int,ss) for ss in split(readline(f))] - AMa = zeros(nAMa) - Acl = zeros(nAcl) - Aτ = zeros(nAτ) + AMa = zeros(nAMa) # array of Mach numbers in database + Acl = zeros(nAcl) # array of cl in database + Aτ = zeros(nAτ) # array of t/c in database A = zeros(nAMa, nAcl, nAτ, nAfun) @inbounds for i = 1:nAMa @@ -29,7 +38,7 @@ function airtable(fname) Aτ[i] = parse(Float64, readline(f)) end - #Read in Reynolds number + # Read in Reynolds number ARe = parse(Float64, readline(f)) #Read in airfoil data @@ -41,21 +50,69 @@ function airtable(fname) end end - close(f) +close(f) - # Create spline objects to make it faster for airfun.jl since this does not need to be computed each time +# --------------------- + A_M = zeros(nAMa, nAcl, nAτ, nAfun) + A_τ = zeros(nAMa, nAcl, nAτ, nAfun) + A_cl = zeros(nAMa, nAcl, nAτ, nAfun) + A_M_τ = zeros(nAMa, nAcl, nAτ, nAfun) + A_M_cl = zeros(nAMa, nAcl, nAτ, nAfun) + A_cl_τ = zeros(nAMa, nAcl, nAτ, nAfun) +A_M_cl_τ = zeros(nAMa, nAcl, nAτ, nAfun) +# Iterate over the 3 functions - cdf, cdp and cm +for l = 1:nAfun + for k = 1:nAτ + for j = 1:nAcl + A_M[:, j, k, l] = spline(AMa, A[:, j, k, l]) # This gets the derivatives ∂cdf/∂M, ∂cdp/∂M, ∂cm/∂M + end + end - ∂cdf_∂M = Array{Spline1D, 2}(undef, nAcl, nAτ) - ∂cdp_∂M = Array{Spline1D, 2}(undef, nAcl, nAτ) - ∂cm_∂M = Array{Spline1D, 2}(undef, nAcl, nAτ) + for k = 1:nAτ + for i = 1:nAMa + # for j = 1:nAcl + f = A[i, :, k, l] + f_M = A_M[i, :, k, l] + A_cl[i, :, k, l] = spline(Acl, f) + A_M_cl[i, :, k, l] = spline(Acl, f_M) + end + end - @inbounds for k = 1:nAτ - @inbounds for j = 1:nAcl - ∂cdf_∂M[j, k] = Spline1D(AMa, A[:,j,k,1], k = 3) - ∂cdp_∂M[j, k] = Spline1D(AMa, A[:,j,k,2], k = 3) - ∂cm_∂M[j, k] = Spline1D(AMa, A[:,j,k,3], k = 3) + for j = 1:nAcl + for i = 1:nAMa + f = A[i, j, :, l] + f_M = A_M[i, j, :, l] + A_τ[i, j, :, l] = spline(Aτ, f) + A_M_τ[i, j, :, l] = spline(Aτ, f_M) + end + end + + for i = 1:nAMa + for j = 1:nAcl + f = A_cl[i, j, :, l] + f_M = A_M_cl[i, j, :, l] + A_cl_τ[i, j, :, l] = spline(Aτ, f) + A_M_cl_τ[i, j, :, l] = spline(Aτ, f_M) + end + for k = 1:nAτ + f = A_τ[i, :, k, l] + f_M = A_M_τ[i, :, k, l] + A_cl_τ[i, :, k, l] = 0.5*( A_cl_τ[i, :, k, l] + spline(Acl, f)) + A_M_cl_τ[i, :, k, l] = 0.5*(A_M_cl_τ[i, :, k, l] + spline(Acl, f_M)) end end -return nAMa, nAcl, nAτ, nAfun, AMa, Acl, Aτ, A, ∂cdf_∂M, ∂cdp_∂M, ∂cm_∂M + +end + +return airfoil(AMa, Acl, Aτ, ARe, + A, + A_M, + A_τ, + A_cl, + A_M_τ, + A_M_cl, + A_cl_τ, + A_M_cl_τ) end + diff --git a/src/aero/airtable2.jl b/src/aero/airtable2.jl deleted file mode 100644 index e8a314a1..00000000 --- a/src/aero/airtable2.jl +++ /dev/null @@ -1,120 +0,0 @@ -""" - airtable(fname) - -Reads airfoil file and outputs the matrix and splines as an `airfoil`. - -The airfoil data is stored as a function of three variables, typically -Mach number ``\\mathrm{Ma}``, lift coefficient ``c_l``, and thickness to chord ratio ``\\tau``. - - cdf(Ma, cl, τ), cdp(Ma, cl, τ), cm(Ma, cl, τ) - -!!! details "🔃 Inputs and Outputs" - **Inputs:** - - `fname::String`: Path to file. - - **Outputs:** - - `airf::TASOPT.aerodynamics.airfoil`: struct with airfoil performance characteristics. - -!!! compat "Future Changes" - Deprecates `airtable` in `airtable.jl`. The current file will be renamed. -""" -function airtable(fname) - -# Read airfoil data -f = open(fname) - - nAMa::Int, nAcl::Int, nAτ::Int, nAfun::Int = [parse(Int,ss) for ss in split(readline(f))] - - AMa = zeros(nAMa) # array of Mach numbers in database - Acl = zeros(nAcl) # array of cl in database - Aτ = zeros(nAτ) # array of t/c in database - A = zeros(nAMa, nAcl, nAτ, nAfun) - - @inbounds for i = 1:nAMa - AMa[i] = parse(Float64, readline(f)) - end - @inbounds for i=1:nAcl - Acl[i] = parse(Float64, readline(f)) - end - @inbounds for i=1:nAτ - Aτ[i] = parse(Float64, readline(f)) - end - - # Read in Reynolds number - ARe = parse(Float64, readline(f)) - - #Read in airfoil data - @inbounds for k = 1:nAτ - @inbounds for j = 1:nAcl - @inbounds for i = 1:nAMa - A[i,j,k,:] = [parse(Float64,ss) for ss in split(readline(f))] - end - end - end - -close(f) - -# --------------------- - A_M = zeros(nAMa, nAcl, nAτ, nAfun) - A_τ = zeros(nAMa, nAcl, nAτ, nAfun) - A_cl = zeros(nAMa, nAcl, nAτ, nAfun) - A_M_τ = zeros(nAMa, nAcl, nAτ, nAfun) - A_M_cl = zeros(nAMa, nAcl, nAτ, nAfun) - A_cl_τ = zeros(nAMa, nAcl, nAτ, nAfun) -A_M_cl_τ = zeros(nAMa, nAcl, nAτ, nAfun) -# Iterate over the 3 functions - cdf, cdp and cm -for l = 1:nAfun - for k = 1:nAτ - for j = 1:nAcl - A_M[:, j, k, l] = spline(AMa, A[:, j, k, l]) # This gets the derivatives ∂cdf/∂M, ∂cdp/∂M, ∂cm/∂M - end - end - - for k = 1:nAτ - for i = 1:nAMa - # for j = 1:nAcl - f = A[i, :, k, l] - f_M = A_M[i, :, k, l] - A_cl[i, :, k, l] = spline(Acl, f) - A_M_cl[i, :, k, l] = spline(Acl, f_M) - end - end - - for j = 1:nAcl - for i = 1:nAMa - f = A[i, j, :, l] - f_M = A_M[i, j, :, l] - A_τ[i, j, :, l] = spline(Aτ, f) - A_M_τ[i, j, :, l] = spline(Aτ, f_M) - end - end - - for i = 1:nAMa - for j = 1:nAcl - f = A_cl[i, j, :, l] - f_M = A_M_cl[i, j, :, l] - A_cl_τ[i, j, :, l] = spline(Aτ, f) - A_M_cl_τ[i, j, :, l] = spline(Aτ, f_M) - end - for k = 1:nAτ - f = A_τ[i, :, k, l] - f_M = A_M_τ[i, :, k, l] - A_cl_τ[i, :, k, l] = 0.5*( A_cl_τ[i, :, k, l] + spline(Acl, f)) - A_M_cl_τ[i, :, k, l] = 0.5*(A_M_cl_τ[i, :, k, l] + spline(Acl, f_M)) - end - end - - -end - -return airfoil(AMa, Acl, Aτ, ARe, - A, - A_M, - A_τ, - A_cl, - A_M_τ, - A_M_cl, - A_cl_τ, - A_M_cl_τ) -end - diff --git a/src/aero/blax.jl b/src/aero/blax.jl index 4b284485..8d5298b7 100644 --- a/src/aero/blax.jl +++ b/src/aero/blax.jl @@ -5,153 +5,208 @@ Axisymmetric boundary layer + wake calculation routine. Uses specified inviscid velocity, corrects for viscous displacement to allow calculation of separated flow. -!!! compat "Future Changes" - Deprecated by faster [`blax2`](@ref). Will be removed in a future revision. -""" -function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) - - - uei = @MVector zeros(ndim) - rhi = @MVector zeros(ndim) - dsi = @MVector zeros(ndim) - thi = @MVector zeros(ndim) - tsi = @MVector zeros(ndim) - dci = @MVector zeros(ndim) - cfi = @MVector zeros(ndim) - cdi = @MVector zeros(ndim) - cti = @MVector zeros(ndim) - hki = @MVector zeros(ndim) - phi = @MVector zeros(ndim) - - # aa = @MMatrix zeros(3,3) - # bb = @MMatrix zeros(3,3) - # rr = @MVector zeros(3) +!!! details "🔃 Inputs and Outputs" + **Inputs:** + - `ndim::Integer`: physical array dimension. + - `n::Integer`: number of boundary layer + wake points. + - `ite::Integer`: index of trailing edge point, start of wake. + - `xi::Array{Float64}`: arc length array (BL coordinate). + - `bi::Array{Float64}`: lateral width of BL at surface (i.e., body perimeter). ``b_i`` = 0 for wake, 1 for 2D. + - `rni::Array{Float64}`: ``dr/dn`` to account for near-axisymmetric bodies, 0 for 2D. + - `uinv::Array{Float64}`: inviscid velocity, ``u_{inv}``. + - `Reyn::Float64`: Reynolds number, ``\\rho_{ref} u_{ref} l_{ref} / \\mu_{ref}``. + - `Mach::Float64`: Mach number, ``M = u_{ref} / a_{ref}``. + - `fexcr::Float64`: excrescence multiplier applied to wall ``c_f``, 1 for smooth wall. + + Assumed units for all quantities: + - `l_ref`: same unit as used for input `xi`,`bi`. + - `u_ref`: freestream velocity. + - `a_ref`: freestream speed of sound. + - `rho_ref`: freestream density. + - `mu_ref`: freestream viscosity. + **Outputs:** + - `uei::Array{Float64}`: edge velocity, (``u_{e,i} = u_{inv,i} +`` {displacement correction}). + - `dsi::Array{Float64}`: displacement thickness (``\\delta^*``). + - `thi::Array{Float64}`: momentum thickness (``\\theta``). + - `tsi::Array{Float64}`: kinetic energy thickness (``\\theta^*``). + - `dci::Array{Float64}`: density flux thickness (``\\delta^{**}``). + - `cfi::Array{Float64}`: skin friction coefficient, normalized with local ``\\rho``, ``u`` (``c_{f,i}``). + - `cdi::Array{Float64}`: dissipation coefficient , normalized with local ``\\rho``,``u`` (``c_{\\mathcal{D},i}``). + - `cti::Array{Float64}`: max shear-stress coefficient, normalized with local ``\\rho``,``u`` (``c_{t,i}``). + - `hki::Array{Float64}`: kinematic shape parameter (``H_{K,i}``). + - `phi::Array{Float64}`: integrated dissipation (``\\Phi``). + + + Other outputs of interest can be computed as follows. + These are in units of `l_ref`, `rho_ref`, `u_ref` + + - `beffi`: Effective perimeter, ``b_{eff,i} = b_i + 2 \\pi \\delta^* dr/dn``. + - `rhi`: Edge density, ``\\rho_i = (1 + \\frac{(\\gamma-1)}{2}M^2 (1.0-u_{e,i}^2))^\\frac{1}{(\\gamma-1)}``. + - `mdef`: Total mass defect, ``\\rho_i u_{e,i} \\delta^* b_{eff}``. + - `Pdef`: Total momentum defect, ``\\rho_i u_{e,i}^2 \\theta b_{eff}``. + - `Edef`: Total kinetic energy defect, ``\\frac{1}{2} \\rho_i u_{e,i}^3 \\theta^* b_{eff}``. + - `tauwb`: Wall shear force/span, ``\\frac{\\tau_w}{b} = \\frac{1}{2} u_{e,i}^2 c_{f,i} b_{eff}``. + - `Diss`: Dissipation integral, ``\\rho_i u_{e,i}^3 c_{\\mathcal{D},i} b_{eff,i}``. + + Body profile drag `D_p` is the far-downstream momentum defect ``P_\\infty``, + best obtained by applying Squire-Young to the last wake point, ``i = n`` : + + - ``P_{end} = \\rho_i u_{e,i}^2 \\theta b_{eff}`` + - ``H_{end} = \\delta^*/\\theta`` + - ``H_{\\infty} = 1 + (\\gamma-1) M^2`` + - ``H_{avg} = \\frac{1}{2} (H_{end} + H_{inf})`` + - ``P_{inf} = P_{end} u_{e,i}^{H_{avg}} = D_p`` + +See Section 4 of [Simplified Viscous/Inviscid Analysis for Nearly-Axisymmetric Bodies](../assets/drela_TASOPT_2p16/axibl.pdf). +See also [`blsys`](@ref) and [`blvar`](@ref). Deprecates `blax`. +""" +function blax(ndim, n, ite, xᵢ, bi, rni, uinv, Reyn, Mach, fexcr ) + + uₑᵢ = zeros(ndim) + ρᵢ = zeros(ndim) + δᵢ = zeros(ndim) + θᵢ = zeros(ndim) + θsᵢ = zeros(ndim) + δssᵢ = zeros(ndim) + cfi = zeros(ndim) + cdi = zeros(ndim) + cti = zeros(ndim) + hki = zeros(ndim) + ϕ = zeros(ndim) + + aa = zeros(3,3) + bb = zeros(3,3) + rr = zeros(3) + hm, hm_thm, hm_dsm = 1e20*ones(3) hkm, hkm_thm, hkm_dsm, hkm_uem = 0*1e20*ones(4) hcm, hcm_thm, hcm_dsm, hcm_uem = 1e20*ones(4) hsm, hsm_thm, hsm_dsm, hsm_uem = 1e20*ones(4) cfm, cfm_thm, cfm_dsm, cfm_uem = 1e20*ones(4) dim, dim_thm, dim_dsm, dim_uem = 1e20*ones(4) - h , h_th, h_ds, + h , ∂h∂θ, ∂h∂δ, hk, hk_th, hk_ds, hk_ue, hc, hc_th, hc_ds, hc_ue, hs, hs_th, hs_ds, hs_ue, cf, cf_th, cf_ds, cf_ue, di, di_th, di_ds, di_ue = 1e20*ones(23) - + idim = 60 mdi = zeros(idim) uvis = zeros(idim) uvis_mdi = zeros(idim,idim) - dthi = zeros(idim) + dθᵢ = zeros(idim) dmdi = zeros(idim) - duei = zeros(idim) - ddsi = zeros(idim) + duₑᵢ = zeros(idim) + dδᵢ = zeros(idim) - kdim = 3*n # instead of idim + kdim=3*n #idim asys = zeros(kdim,kdim) rsys = zeros(kdim) - - simi, lami, wake, direct = true, true, true, true -#---- pi and 1/(4 pi) - qopi = 1/(4*pi) - gam = 1.4 - gmi = gam - 1.0 + simi, lami, wake, direct = true, true, true, true + +#---- π and 1/(4 π) + π¼ = 0.07957747154594766788444188168625718 + ɣ = 1.4 + + hksep = 2.9 - hksep = 2.9 - eps = 1.0e-6 # Tolerance for Newton solver + ε = 1.0e-6 - if(n > idim) + if(n > idim) println("BLAX: Local array overflow. Increase idim to", n) quit() end - -#---- initialize ue to inviscid uinv, and initialize rhoe - uei[1:n] = uinv[1:n] - rhi = @. (1 + 0.5*gmi*Mach^2 * (1.0 - uei^2))^(1.0/gmi) - - # @inbounds for i = 1:n - # uei[i] = uinv[i] - # trat = 1.0 + 0.5*gmi*Mach^2 * (1.0-uei[i]^2) - # rhi[i] = trat^(1.0/gmi) - # end - -#---- first point is not calculated if xi=0 there - if(xi[1] == 0.0) - thi[1] = 0. - dsi[1] = 0. + + gmi = ɣ - 1.0 + +#---- initialize ue to inviscid uinv, and initialize ρe + for i = 1: n + uₑᵢ[i] = uinv[i] + + trat = 1.0 + 0.5*gmi*Mach^2 * (1.0-uₑᵢ[i]^2) + ρᵢ[i] = trat^(1.0/gmi) + end + +#---- first point is not calculated if xᵢ=0 there + if(xᵢ[1] == 0.0) + θᵢ[1] = 0. + δᵢ[1] = 0. mdi[1] = 0. - phi[1] = 0. + ϕ[1] = 0. end # ============================================================================= #---- sweep downstream to initialize BL via standard BL march, -#- fudging by specifying plausible Hk if separation occurs (Goldstein singularity) -#- (this is to provide an intial guess only, later the global system is solved simultaneously via Newton iteration) +#- fudging by specifying plausible Hk if separation occurs + +direct = true +for i = 2: n #BL march loop - direct = true - @inbounds for i = 2:n + simi = xᵢ[i-1] == 0.0 + +#c lami = simi # laminar similarity station + lami = false # turbulent similarity station - simi = xi[i-1] == 0.0 -#c lami = simi # laminar similarity station - lami = false # turbulent similarity station wake = i > ite - x = xi[i] #xlocation - b = bi[i] #perimeter - rn = rni[i] #dr/dn -#[prash] previous points x minus - xm = xi[i-1] + x = xᵢ[i] + b = bi[i] + rn = rni[i] + + xm = xᵢ[i-1] bm = bi[i-1] rnm = rni[i-1] #------ set i-1 station, and initialize station i for iteration - if(simi) + if(simi) uem = 0. thm = 0. dsm = 0. - ue = uei[i] + ue = uₑᵢ[i] rex = ue*x * Reyn th = 0.4*x / sqrt(rex) ds = th * 2.0 else - uem = uei[i-1] - thm = thi[i-1] - dsm = dsi[i-1] + uem = uₑᵢ[i-1] + thm = θᵢ[i-1] + dsm = δᵢ[i-1] - th = thi[i-1] - ds = dsi[i-1] - if(direct) + th = θᵢ[i-1] + ds = δᵢ[i-1] + if(direct) #-------- previous station was direct... use specified ue as initial guess - ue = uei[i] + ue = uₑᵢ[i] else #-------- previous station was inverse... use previous-station ue as initial guess - ue = uei[i-1] + ue = uₑᵢ[i-1] end end + #------ always try direct mode first direct = true hkprev = 0. - @inbounds for iter = 1:20 - (h , h_th, h_ds, + for iter = 1: 20 #Newton iteration + + (h , ∂h∂θ, ∂h∂δ, hk, hk_th, hk_ds, hk_ue, hc, hc_th, hc_ds, hc_ue, hs, hs_th, hs_ds, hs_ue, cf, cf_th, cf_ds, cf_ue, di, di_th, di_ds, di_ue ) = blvar(simi,lami,wake, Reyn,Mach, fexcr, x, th ,ds ,ue) - if(iter == 1) + if(iter==1) hkprev = hk else - if(hk > hksep) # & hk > hkprev) -#---------- Hk limit exceeded... switch to inverse mode for this point + if(hk > hksep) # .and. hk > hkprev) +#---------- Hk limit exceeded... switch to inverse mode for θᵢs point direct = false end end @@ -159,7 +214,7 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) #-------- set up 2-point differenced BL equation system aa, bb, rr = blsys(simi,lami,wake,direct, Mach, uinv[i],hksep, x,b,rn,th,ds,ue, - h , h_th, h_ds, + h , ∂h∂θ, ∂h∂δ, hk, hk_th, hk_ds, hk_ue, hc, hc_th, hc_ds, hc_ue, hs, hs_th, hs_ds, hs_ue, @@ -172,46 +227,53 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) hsm, hsm_thm, hsm_dsm, hsm_uem, cfm, cfm_thm, cfm_dsm, cfm_uem, dim, dim_thm, dim_dsm, dim_uem) - - rr = aa\rr #solve linear system + + rr = aa\rr dth = -rr[1] dds = -rr[2] due = -rr[3] rlx = 1.0 - - if(rlx*dth > 1.6*th) rlx = 1.6*th/dth; end - if(rlx*dth < -0.6*th) rlx = -0.6*th/dth; end - if(rlx*dds > 2.5*ds) rlx = 2.5*ds/dds; end - if(rlx*dds < -0.4*ds) rlx = -0.4*ds/dds; end - if(rlx*due > 0.2*ue) rlx = 0.2*ue/due; end - if(rlx*due < -0.1*ue) rlx = -0.1*ue/due; end + + if(rlx*dth > 1.6*th) rlx = 1.6*th/dth ; end + if(rlx*dth < -0.6*th) rlx = -0.6*th/dth ; end + if(rlx*dds > 2.5*ds) rlx = 2.5*ds/dds ; end + if(rlx*dds < -0.4*ds) rlx = -0.4*ds/dds ; end + if(rlx*due > 0.2*ue) rlx = 0.2*ue/due ; end + if(rlx*due < -0.1*ue) rlx = -0.1*ue/due ; end dmax = max( abs(dth)/th , abs(dds)/ds , abs(due)/ue ) - + +# if(iter==1) write(*,*) +# rt = ue*th*Reyn +# write(*,1200) iter, direct, dmax, rlx, ue, hk, rt, cf, di +# 1200 format(1x,i4, l2, e12.4, 9g13.5) th = th + rlx*dth ds = ds + rlx*dds ue = ue + rlx*due - - if(dmax < eps) break end - - end # end iter loop - uei[i] = ue - dsi[i] = ds - thi[i] = th - tsi[i] = hs*th - dci[i] = hc*th + if(dmax < ε) + break; + end + end #newton iteration + + + uₑᵢ[i] = ue + δᵢ[i] = ds + θᵢ[i] = th + θsᵢ[i] = hs*th + δssᵢ[i] = hc*th cfi[i] = cf cdi[i] = di*hs/2.0 cti[i] = 0.03 * 0.5*hs*((hk-1.0)/hk)^2 hki[i] = hk - dib = cdi[i] *rhi[i] *uei[i]^3 * (b + 2.0*pi*ds *rn ) - dibm = cdi[i-1]*rhi[i-1]*uei[i-1]^3 * (bm + 2.0*pi*dsm*rnm) - phi[i] = phi[i-1] + 0.5*(dib + dibm) * (x - xm) - mdi[i] = ue*ds*(b + 2.0*pi*ds) + 𝒟ᵢb = cdi[i] *ρᵢ[i] *uₑᵢ[i]^3 * (b + 2.0*π*ds *rn ) + 𝒟ᵢbm = cdi[i-1]*ρᵢ[i-1]*uₑᵢ[i-1]^3 * (bm + 2.0*π*dsm*rnm) + ϕ[i] = ϕ[i-1] + 0.5*(𝒟ᵢb + 𝒟ᵢbm) * (x - xm) + mdi[i] = ue*ds*(b + 2.0*π*ds) + thm = th dsm = ds @@ -219,8 +281,8 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) uem = ue hm = h - hm_thm = h_th - hm_dsm = h_ds + hm_thm = ∂h∂θ + hm_dsm = ∂h∂δ hkm = hk hkm_thm = hk_th @@ -242,7 +304,7 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) dim_dsm = di_ds dim_uem = di_ue - if(i >= ite) + if(i>=ite) cfm = 0. cfm_thm = 0. cfm_dsm = 0. @@ -254,7 +316,7 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) cfm_uem = cf_ue end - end #end i loop +end # BL march loop # ============================================================================= @@ -265,25 +327,40 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) nsys = 3*n #---- clear and accumulate source-influence matrix - uvis_mdi=zeros(n,n) - @inbounds for i = 1:n - @inbounds for j = 1: n-1 - dx = xi[i] - 0.5*(xi[j+1]+xi[j]) - uvis_mdi[i,j+1] = uvis_mdi[i,j+1] + qopi/(dx*abs(dx)) - uvis_mdi[i,j ] = uvis_mdi[i,j ] - qopi/(dx*abs(dx)) + for i = 1: n + for j = 1: n + uvis_mdi[i,j] = 0. end end + + for i = 1: n + for j = 1: n-1 + dx = xᵢ[i] - 0.5*(xᵢ[j+1]+xᵢ[j]) +# dm = mdi(j+1) - mdi[j] +# du = dm * π¼ / (dx*abs(dx)) +# duₑᵢ = duₑᵢ + du + uvis_mdi[i,j+1] = uvis_mdi[i,j+1] + π¼/(dx*abs(dx)) + uvis_mdi[i,j ] = uvis_mdi[i,j ] - π¼/(dx*abs(dx)) + end + end + +# i = 15 +# for j = 1: n +# write(*,*) i, j, uvis_mdi[i,j] +# end -# print("15, :", uvis_mdi[15,:]) #------------------------------------------------------------ #---- global Newton iteration - npass = 20 - @inbounds for ipass = 1:npass + npass = 20 + for ipass = 1: npass #Newton iteration #---- clear system matrix and righthand side - rsys = zeros(nsys) - asys = zeros(nsys,nsys) - + for k = 1: nsys + rsys[k] = 0. + for l = 1: nsys + asys[k,l] = 0. + end + end #---- first point variables are held frozen... put 1's on diagonal asys[1,1] = 1.0 @@ -292,41 +369,45 @@ function blax(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) #---- set current uvis corresponding to current mdi - dsi[1] = 0. - - @inbounds for i = 2: n + δᵢ[1] = 0. + for i = 2: n uvis[i] = uinv[i] - @inbounds for j = 1: n + for j = 1: n uvis[i] = uvis[i] + uvis_mdi[i,j]*mdi[j] end end #---- sweep downstream to set up BL equations -for i = 2:n - - simi = xi[i-1] == 0.0 + for i = 2: n # Set up BL loop + simi = xᵢ[i-1] == 0.0 + #c lami = simi lami = false + wake = i > ite - x = xi[i] + x = xᵢ[i] b = bi[i] rn = rni[i] - th = thi[i] + th = θᵢ[i] md = mdi[i] - ue = uei[i] + ue = uₑᵢ[i] - xm = xi[i-1] + xm = xᵢ[i-1] bm = bi[i-1] rnm = rni[i-1] - thm = thi[i-1] + thm = θᵢ[i-1] mdm = mdi[i-1] - uem = uei[i-1] + uem = uₑᵢ[i-1] +#c md = ue*ds*(b + 2.0*π*ds*rn) - bp = b * 0.25/pi - mpu = 0.5*md/(pi*ue) - if(rn <= 1.0e-6) +#c md/(ue*2*π) = ds*(b/2π + ds*rn) +#c 0.5 rn ds^2 + (b/4π)*ds - md/(4π ue) = 0 +#c ds = ( sqrt(bp^2 + 0.5*md/(π*ue)) - bp ) / rn + bp = b * 0.25/π + mpu = 0.5*md/(π*ue) + if(rn <= 1.0e-6) ds = md/(ue*b) ds_md = 1.0/(ue*b) ds_ue = -ds/ue @@ -336,35 +417,46 @@ for i = 2:n ds_ue = 0.5/sqrt(bp^2 + mpu) * (-mpu/ue) / rn end - if(simi) + if(simi) dsm = 0. dsm_mdm = 0. dsm_uem = 0. else - if(rnm <= 1.0e-6) + if(rnm <= 1.0e-6) dsm = mdm/(uem*bm) dsm_mdm = 1.0/(uem*bm) dsm_uem = -dsm/uem else - bpm = bm * 0.25/pi - mpum = 0.5*mdm/(pi*uem) + bpm = bm * 0.25/π + mpum = 0.5*mdm/(π*uem) dsm = (sqrt(bpm^2 + mpum) - bpm) / rnm dsm_mdm = 0.5/sqrt(bpm^2 + mpum) * ( mpum/mdm) / rnm dsm_uem = 0.5/sqrt(bpm^2 + mpum) * (-mpum/uem) / rnm end end - - (h , h_th, h_ds, + +# if(.not.simi) +# call blvar(simi,lami,wake, Reyn,Mach, fexcr, +# & xm, thm ,dsm ,uem , +# & hm, hm_thm, hm_dsm, +# & hkm, hkm_thm, hkm_dsm, hkm_uem, +# & hcm, hcm_thm, hcm_dsm, hcm_uem, +# & hsm, hsm_thm, hsm_dsm, hsm_uem, +# & cfm, cfm_thm, cfm_dsm, cfm_uem, +# & dim, dim_thm, dim_dsm, dim_uem ) +# end + + (h , ∂h∂θ, ∂h∂δ, hk, hk_th, hk_ds, hk_ue, hc, hc_th, hc_ds, hc_ue, hs, hs_th, hs_ds, hs_ue, cf, cf_th, cf_ds, cf_ue, di, di_th, di_ds, di_ue ) = blvar(simi,lami,wake, Reyn,Mach, fexcr,x, th ,ds ,ue) - direct = true + aa,bb,rr = blsys(simi,lami,wake,direct, Mach, uinv[i],hksep, x,b,rn,th,ds,ue, - h , h_th, h_ds, + h , ∂h∂θ, ∂h∂δ, hk, hk_th, hk_ds, hk_ue, hc, hc_th, hc_ds, hc_ue, hs, hs_th, hs_ds, hs_ue, @@ -379,8 +471,8 @@ for i = 2:n dim, dim_thm, dim_dsm, dim_uem) #------ put BL equations of small 3x3 system into big system - @inbounds for k = 1:2 - ksys = 3*(i-1) + k + for k = 1: 2 + ksys = 3*(i-1)+ k rsys[ksys] = rr[k] r_th = aa[k,1] @@ -409,7 +501,7 @@ for i = 2:n ksys = 3*(i-1) + k rsys[ksys] = ue - uvis[i] - @inbounds for j = 1:n + for j = 1: n lsys = 3*(j-1) + 2 asys[ksys,lsys] = -uvis_mdi[i,j] end @@ -418,8 +510,8 @@ for i = 2:n asys[ksys,lsys] = asys[ksys,lsys] + 1.0 #------ also store dependent variables for returning - tsi[i] = hs*th - dci[i] = hc*th + θsᵢ[i] = hs*th + δssᵢ[i] = hc*th cfi[i] = cf cdi[i] = di*hs/2.0 cti[i] = 0.03 * 0.5*hs*((hk-1.0)/hk)^2 @@ -427,8 +519,8 @@ for i = 2:n #------ set dependent i-1 variables for next interval hm = h - hm_thm = h_th - hm_dsm = h_ds + hm_thm = ∂h∂θ + hm_dsm = ∂h∂δ hkm = hk hkm_thm = hk_th @@ -445,7 +537,7 @@ for i = 2:n hcm_dsm = hc_ds hcm_uem = hc_ue - if(i >= ite) + if(i>=ite) cfm = 0. cfm_thm = 0. cfm_dsm = 0. @@ -462,82 +554,99 @@ for i = 2:n dim_dsm = di_ds dim_uem = di_ue -end #end i = 2:n loop + end #end BL loop -# do i = 1, n -# k1 = 3*(i-1) + 1 -# k2 = 3*(i-1) + 2 -# k3 = 3*(i-1) + 3 +# for i = 1: n +# k1 = 3*[i-1] + 1 +# k2 = 3*[i-1] + 2 +# k3 = 3*[i-1] + 3 # write(*,'(1x,i4,3e12.4,3x,3g15.7)') -# & i, rsys(k1),rsys(k2),rsys(k3), uei[i], uvis[i], uei[i]-uvis[i] +# & i, rsys(k1),rsys(k2),rsys(k3), uₑᵢ[i], uvis[i], uₑᵢ[i]-uvis[i] # end #---- solve Newton system - rsys = asys\rsys #call gaussn(kdim,nsys,asys,rsys,1) +# call gaussn(kdim,nsys,asys,rsys,1) -#---- set Newton changes, set max change >dmax, and set limiter rlx +rsys = asys\rsys + +#---- set Newton changes, set max change dmax, and set limiter rlx dmax = 0. rlx = 1.0 - @inbounds for i = 2:n + for i = 2: n b = bi[i] - th = thi[i] + th = θᵢ[i] md = mdi[i] - ue = uei[i] + ue = uₑᵢ[i] kth = 3*(i-1) + 1 kmd = 3*(i-1) + 2 kue = 3*(i-1) + 3 - dthi[i] = -rsys[kth] + dθᵢ[i] = -rsys[kth] dmdi[i] = -rsys[kmd] - duei[i] = -rsys[kue] + duₑᵢ[i] = -rsys[kue] - bp = b * 0.25/pi - mpu = 0.5*md/(pi*ue) + bp = b * 0.25/π + mpu = 0.5*md/(π*ue) ds = sqrt(bp^2 + mpu) - bp ds_md = 0.5/sqrt(bp^2 + mpu) * ( mpu/md) ds_ue = 0.5/sqrt(bp^2 + mpu) * (-mpu/ue) - ddsi[i] = ds_md*dmdi[i] + ds_ue*duei[i] +# ds = md/(b*ue) +# ds_md = 1.0/(b*ue) +# ds_ue = -ds/ue - if(rlx*dthi[i] > 1.6*th) rlx = 1.6*th/dthi[i] end - if(rlx*dthi[i] < -0.6*th) rlx = -0.6*th/dthi[i] end - if(rlx*ddsi[i] > 2.5*ds) rlx = 2.5*ds/ddsi[i] end - if(rlx*ddsi[i] < -0.4*ds) rlx = -0.4*ds/ddsi[i] end - if(rlx*duei[i] > 0.2*ue) rlx = 0.2*ue/duei[i] end - if(rlx*duei[i] < -0.1*ue) rlx = -0.1*ue/duei[i] end - -# println(i, ", ", rlx) - dmax = max( dmax , abs(dthi[i])/th , abs(ddsi[i])/ds , abs(duei[i])/ue) -# println("dmax = $dmax, ue = $ue") + dδᵢ[i] = ds_md*dmdi[i] + ds_ue*duₑᵢ[i] + + if(rlx*dθᵢ[i] > 1.6*th) rlx = 1.6*th/dθᵢ[i]; end + if(rlx*dθᵢ[i] < -0.6*th) rlx = -0.6*th/dθᵢ[i]; end + if(rlx*dδᵢ[i] > 2.5*ds) rlx = 2.5*ds/dδᵢ[i]; end + if(rlx*dδᵢ[i] < -0.4*ds) rlx = -0.4*ds/dδᵢ[i]; end + if(rlx*duₑᵢ[i] > 0.2*ue) rlx = 0.2*ue/duₑᵢ[i]; end + if(rlx*duₑᵢ[i] < -0.1*ue) rlx = -0.1*ue/duₑᵢ[i]; end + + dmax = max( dmax , abs(dθᵢ[i])/th , + abs(dδᵢ[i])/ds , + abs(duₑᵢ[i])/ue ) end #------ perform Newton updated, with limiter if rlx < 1 - @inbounds for i = 2:n - thi[i] = thi[i] + rlx*dthi[i] - dsi[i] = dsi[i] + rlx*ddsi[i] - uei[i] = uei[i] + rlx*duei[i] - mdi[i] = uei[i]*dsi[i]*(bi[i] + 2.0*pi*dsi[i]*rni[i]) + for i = 2: n + θᵢ[i] = θᵢ[i] + rlx*dθᵢ[i] + δᵢ[i] = δᵢ[i] + rlx*dδᵢ[i] + uₑᵢ[i] = uₑᵢ[i] + rlx*duₑᵢ[i] + mdi[i] = uₑᵢ[i]*δᵢ[i]*(bi[i] + 2.0*π*δᵢ[i]*rni[i]) end - if(dmax < eps) break end +# for i = 2: n +# θᵢ[i] = θᵢ[i] + rlx*dθᵢ[i] +#cc δᵢ[i] = δᵢ[i] + rlx*dδᵢ[i] +# uₑᵢ[i] = uₑᵢ[i] + rlx*duₑᵢ[i] +# mdi[i] = mdi[i] + rlx*dmdi[i] +# δᵢ[i] = mdi[i]/(bi[i]*uₑᵢ[i]) +# end -end +# if(ipass==1) write(*,*) +# write(*,2200) ipass, dmax, rlx +# 2200 format(1x,i4, e12.4, f8.4) + if(dmax < ε) break; end -#---- integrate running dissipation - phi[1] = 0. - @inbounds for i = 2: n - x = xi[i] - xm = xi[i-1] + end #End newton iteration - dib = cdi[i] *rhi[i] *uei[i]^3 * (bi[i] + 2.0*pi*dsi[i] *rni[i]) - dibm = cdi[i-1]*rhi[i-1]*uei[i-1]^3 * (bi[i-1] + 2.0*pi*dsi[i-1]*rni[i-1]) - phi[i] = phi[i-1] + 0.5*(dib + dibm) * (x - xm) - end - return uei, dsi, thi, tsi, dci, cfi, cdi, cti, hki, phi +#---- integrate running dissipation + ϕ[1] = 0. + for i = 2: n + x = xᵢ[i] + xm = xᵢ[i-1] + + 𝒟ᵢb = cdi[i] *ρᵢ[i] *uₑᵢ[i]^3 * (bi[i] + 2.0*π*δᵢ[i] *rni[i]) + 𝒟ᵢbm = cdi[i-1]*ρᵢ[i-1]*uₑᵢ[i-1]^3 * (bi[i-1] + 2.0*π*δᵢ[i-1]*rni[i-1]) -end # blax + ϕ[i] = ϕ[i-1] + 0.5*(𝒟ᵢb + 𝒟ᵢbm) * (x - xm) + end + return uₑᵢ, δᵢ, θᵢ, θsᵢ, δssᵢ, cfi, cdi, cti, hki, ϕ + end # blax diff --git a/src/aero/blax2.jl b/src/aero/blax2.jl deleted file mode 100644 index 66cb3167..00000000 --- a/src/aero/blax2.jl +++ /dev/null @@ -1,652 +0,0 @@ -""" - blax2(ndim, n,ite, xi, bi, rni, uinv, Reyn, Mach, fexcr) - -Axisymmetric boundary layer + wake calculation routine. -Uses specified inviscid velocity, corrects for viscous -displacement to allow calculation of separated flow. - -!!! details "🔃 Inputs and Outputs" - **Inputs:** - - `ndim::Integer`: physical array dimension. - - `n::Integer`: number of boundary layer + wake points. - - `ite::Integer`: index of trailing edge point, start of wake. - - `xi::Array{Float64}`: arc length array (BL coordinate). - - `bi::Array{Float64}`: lateral width of BL at surface (i.e., body perimeter). ``b_i`` = 0 for wake, 1 for 2D. - - `rni::Array{Float64}`: ``dr/dn`` to account for near-axisymmetric bodies, 0 for 2D. - - `uinv::Array{Float64}`: inviscid velocity, ``u_{inv}``. - - `Reyn::Float64`: Reynolds number, ``\\rho_{ref} u_{ref} l_{ref} / \\mu_{ref}``. - - `Mach::Float64`: Mach number, ``M = u_{ref} / a_{ref}``. - - `fexcr::Float64`: excrescence multiplier applied to wall ``c_f``, 1 for smooth wall. - - Assumed units for all quantities: - - `l_ref`: same unit as used for input `xi`,`bi`. - - `u_ref`: freestream velocity. - - `a_ref`: freestream speed of sound. - - `rho_ref`: freestream density. - - `mu_ref`: freestream viscosity. - - **Outputs:** - - `uei::Array{Float64}`: edge velocity, (``u_{e,i} = u_{inv,i} +`` {displacement correction}). - - `dsi::Array{Float64}`: displacement thickness (``\\delta^*``). - - `thi::Array{Float64}`: momentum thickness (``\\theta``). - - `tsi::Array{Float64}`: kinetic energy thickness (``\\theta^*``). - - `dci::Array{Float64}`: density flux thickness (``\\delta^{**}``). - - `cfi::Array{Float64}`: skin friction coefficient, normalized with local ``\\rho``, ``u`` (``c_{f,i}``). - - `cdi::Array{Float64}`: dissipation coefficient , normalized with local ``\\rho``,``u`` (``c_{\\mathcal{D},i}``). - - `cti::Array{Float64}`: max shear-stress coefficient, normalized with local ``\\rho``,``u`` (``c_{t,i}``). - - `hki::Array{Float64}`: kinematic shape parameter (``H_{K,i}``). - - `phi::Array{Float64}`: integrated dissipation (``\\Phi``). - - - Other outputs of interest can be computed as follows. - These are in units of `l_ref`, `rho_ref`, `u_ref` - - - `beffi`: Effective perimeter, ``b_{eff,i} = b_i + 2 \\pi \\delta^* dr/dn``. - - `rhi`: Edge density, ``\\rho_i = (1 + \\frac{(\\gamma-1)}{2}M^2 (1.0-u_{e,i}^2))^\\frac{1}{(\\gamma-1)}``. - - `mdef`: Total mass defect, ``\\rho_i u_{e,i} \\delta^* b_{eff}``. - - `Pdef`: Total momentum defect, ``\\rho_i u_{e,i}^2 \\theta b_{eff}``. - - `Edef`: Total kinetic energy defect, ``\\frac{1}{2} \\rho_i u_{e,i}^3 \\theta^* b_{eff}``. - - `tauwb`: Wall shear force/span, ``\\frac{\\tau_w}{b} = \\frac{1}{2} u_{e,i}^2 c_{f,i} b_{eff}``. - - `Diss`: Dissipation integral, ``\\rho_i u_{e,i}^3 c_{\\mathcal{D},i} b_{eff,i}``. - - Body profile drag `D_p` is the far-downstream momentum defect ``P_\\infty``, - best obtained by applying Squire-Young to the last wake point, ``i = n`` : - - - ``P_{end} = \\rho_i u_{e,i}^2 \\theta b_{eff}`` - - ``H_{end} = \\delta^*/\\theta`` - - ``H_{\\infty} = 1 + (\\gamma-1) M^2`` - - ``H_{avg} = \\frac{1}{2} (H_{end} + H_{inf})`` - - ``P_{inf} = P_{end} u_{e,i}^{H_{avg}} = D_p`` - -See Section 4 of [Simplified Viscous/Inviscid Analysis for Nearly-Axisymmetric Bodies](../assets/drela_TASOPT_2p16/axibl.pdf). -See also [`blsys`](@ref) and [`blvar`](@ref). Deprecates `blax`. -""" -function blax2(ndim, n,ite, xᵢ,bi,rni, uinv, Reyn, Mach, fexcr ) - - uₑᵢ = zeros(ndim) - ρᵢ = zeros(ndim) - δᵢ = zeros(ndim) - θᵢ = zeros(ndim) - θsᵢ = zeros(ndim) - δssᵢ = zeros(ndim) - cfi = zeros(ndim) - cdi = zeros(ndim) - cti = zeros(ndim) - hki = zeros(ndim) - ϕ = zeros(ndim) - - aa = zeros(3,3) - bb = zeros(3,3) - rr = zeros(3) - - hm, hm_thm, hm_dsm = 1e20*ones(3) - hkm, hkm_thm, hkm_dsm, hkm_uem = 0*1e20*ones(4) - hcm, hcm_thm, hcm_dsm, hcm_uem = 1e20*ones(4) - hsm, hsm_thm, hsm_dsm, hsm_uem = 1e20*ones(4) - cfm, cfm_thm, cfm_dsm, cfm_uem = 1e20*ones(4) - dim, dim_thm, dim_dsm, dim_uem = 1e20*ones(4) - h , ∂h∂θ, ∂h∂δ, - hk, hk_th, hk_ds, hk_ue, - hc, hc_th, hc_ds, hc_ue, - hs, hs_th, hs_ds, hs_ue, - cf, cf_th, cf_ds, cf_ue, - di, di_th, di_ds, di_ue = 1e20*ones(23) - - - idim = 60 - mdi = zeros(idim) - uvis = zeros(idim) - uvis_mdi = zeros(idim,idim) - dθᵢ = zeros(idim) - dmdi = zeros(idim) - duₑᵢ = zeros(idim) - dδᵢ = zeros(idim) - - kdim=3*n #idim - asys = zeros(kdim,kdim) - rsys = zeros(kdim) - - simi, lami, wake, direct = true, true, true, true - -#---- π and 1/(4 π) - π¼ = 0.07957747154594766788444188168625718 - ɣ = 1.4 - - hksep = 2.9 - - ε = 1.0e-6 - - if(n > idim) - println("BLAX: Local array overflow. Increase idim to", n) - quit() - end - - gmi = ɣ - 1.0 - -#---- initialize ue to inviscid uinv, and initialize ρe - for i = 1: n - uₑᵢ[i] = uinv[i] - - trat = 1.0 + 0.5*gmi*Mach^2 * (1.0-uₑᵢ[i]^2) - ρᵢ[i] = trat^(1.0/gmi) - end - -#---- first point is not calculated if xᵢ=0 there - if(xᵢ[1] == 0.0) - θᵢ[1] = 0. - δᵢ[1] = 0. - mdi[1] = 0. - ϕ[1] = 0. - end - -# ============================================================================= -#---- sweep downstream to initialize BL via standard BL march, -#- fudging by specifying plausible Hk if separation occurs - -direct = true -for i = 2: n #BL march loop - - simi = xᵢ[i-1] == 0.0 - -#c lami = simi # laminar similarity station - lami = false # turbulent similarity station - - wake = i > ite - - x = xᵢ[i] - b = bi[i] - rn = rni[i] - - xm = xᵢ[i-1] - bm = bi[i-1] - rnm = rni[i-1] - -#------ set i-1 station, and initialize station i for iteration - if(simi) - uem = 0. - thm = 0. - dsm = 0. - - ue = uₑᵢ[i] - rex = ue*x * Reyn - th = 0.4*x / sqrt(rex) - ds = th * 2.0 - - else - uem = uₑᵢ[i-1] - thm = θᵢ[i-1] - dsm = δᵢ[i-1] - - th = θᵢ[i-1] - ds = δᵢ[i-1] - if(direct) -#-------- previous station was direct... use specified ue as initial guess - ue = uₑᵢ[i] - else -#-------- previous station was inverse... use previous-station ue as initial guess - ue = uₑᵢ[i-1] - end - - end - -#------ always try direct mode first - direct = true - hkprev = 0. - - for iter = 1: 20 #Newton iteration - - (h , ∂h∂θ, ∂h∂δ, - hk, hk_th, hk_ds, hk_ue, - hc, hc_th, hc_ds, hc_ue, - hs, hs_th, hs_ds, hs_ue, - cf, cf_th, cf_ds, cf_ue, - di, di_th, di_ds, di_ue ) = blvar(simi,lami,wake, Reyn,Mach, fexcr, x, th ,ds ,ue) - - if(iter==1) - hkprev = hk - else - if(hk > hksep) # .and. hk > hkprev) -#---------- Hk limit exceeded... switch to inverse mode for θᵢs point - direct = false - end - end - -#-------- set up 2-point differenced BL equation system - aa, bb, rr = blsys(simi,lami,wake,direct, Mach, uinv[i],hksep, - x,b,rn,th,ds,ue, - h , ∂h∂θ, ∂h∂δ, - hk, hk_th, hk_ds, hk_ue, - hc, hc_th, hc_ds, hc_ue, - hs, hs_th, hs_ds, hs_ue, - cf, cf_th, cf_ds, cf_ue, - di, di_th, di_ds, di_ue, - xm,bm,rnm,thm,dsm,uem, - hm , hm_thm, hm_dsm, - hkm, hkm_thm, hkm_dsm, hkm_uem, - hcm, hcm_thm, hcm_dsm, hcm_uem, - hsm, hsm_thm, hsm_dsm, hsm_uem, - cfm, cfm_thm, cfm_dsm, cfm_uem, - dim, dim_thm, dim_dsm, dim_uem) - - rr = aa\rr - dth = -rr[1] - dds = -rr[2] - due = -rr[3] - - rlx = 1.0 - - if(rlx*dth > 1.6*th) rlx = 1.6*th/dth ; end - if(rlx*dth < -0.6*th) rlx = -0.6*th/dth ; end - if(rlx*dds > 2.5*ds) rlx = 2.5*ds/dds ; end - if(rlx*dds < -0.4*ds) rlx = -0.4*ds/dds ; end - if(rlx*due > 0.2*ue) rlx = 0.2*ue/due ; end - if(rlx*due < -0.1*ue) rlx = -0.1*ue/due ; end - - dmax = max( abs(dth)/th , abs(dds)/ds , abs(due)/ue ) - -# if(iter==1) write(*,*) -# rt = ue*th*Reyn -# write(*,1200) iter, direct, dmax, rlx, ue, hk, rt, cf, di -# 1200 format(1x,i4, l2, e12.4, 9g13.5) - - th = th + rlx*dth - ds = ds + rlx*dds - ue = ue + rlx*due - - if(dmax < ε) - break; - end - end #newton iteration - - - uₑᵢ[i] = ue - δᵢ[i] = ds - θᵢ[i] = th - θsᵢ[i] = hs*th - δssᵢ[i] = hc*th - cfi[i] = cf - cdi[i] = di*hs/2.0 - cti[i] = 0.03 * 0.5*hs*((hk-1.0)/hk)^2 - hki[i] = hk - - 𝒟ᵢb = cdi[i] *ρᵢ[i] *uₑᵢ[i]^3 * (b + 2.0*π*ds *rn ) - 𝒟ᵢbm = cdi[i-1]*ρᵢ[i-1]*uₑᵢ[i-1]^3 * (bm + 2.0*π*dsm*rnm) - ϕ[i] = ϕ[i-1] + 0.5*(𝒟ᵢb + 𝒟ᵢbm) * (x - xm) - mdi[i] = ue*ds*(b + 2.0*π*ds) - - - thm = th - dsm = ds - hsm = hs - uem = ue - - hm = h - hm_thm = ∂h∂θ - hm_dsm = ∂h∂δ - - hkm = hk - hkm_thm = hk_th - hkm_dsm = hk_ds - hkm_uem = hk_ue - - hsm = hs - hsm_thm = hs_th - hsm_dsm = hs_ds - hsm_uem = hs_ue - - hcm = hc - hcm_thm = hc_th - hcm_dsm = hc_ds - hcm_uem = hc_ue - - dim = di - dim_thm = di_th - dim_dsm = di_ds - dim_uem = di_ue - - if(i>=ite) - cfm = 0. - cfm_thm = 0. - cfm_dsm = 0. - cfm_uem = 0. - else - cfm = cf - cfm_thm = cf_th - cfm_dsm = cf_ds - cfm_uem = cf_ue - end - -end # BL march loop - - -# ============================================================================= -#---- perform global viscous/inviscid iteration with source model -#- for viscous displacement - -#---- size of system - nsys = 3*n - -#---- clear and accumulate source-influence matrix - for i = 1: n - for j = 1: n - uvis_mdi[i,j] = 0. - end - end - - for i = 1: n - for j = 1: n-1 - dx = xᵢ[i] - 0.5*(xᵢ[j+1]+xᵢ[j]) -# dm = mdi(j+1) - mdi[j] -# du = dm * π¼ / (dx*abs(dx)) -# duₑᵢ = duₑᵢ + du - uvis_mdi[i,j+1] = uvis_mdi[i,j+1] + π¼/(dx*abs(dx)) - uvis_mdi[i,j ] = uvis_mdi[i,j ] - π¼/(dx*abs(dx)) - end - end - -# i = 15 -# for j = 1: n -# write(*,*) i, j, uvis_mdi[i,j] -# end - -#------------------------------------------------------------ -#---- global Newton iteration - npass = 20 - for ipass = 1: npass #Newton iteration - -#---- clear system matrix and righthand side - for k = 1: nsys - rsys[k] = 0. - for l = 1: nsys - asys[k,l] = 0. - end - end - -#---- first point variables are held frozen... put 1's on diagonal - asys[1,1] = 1.0 - asys[2,2] = 1.0 - asys[3,3] = 1.0 - - -#---- set current uvis corresponding to current mdi - δᵢ[1] = 0. - for i = 2: n - uvis[i] = uinv[i] - for j = 1: n - uvis[i] = uvis[i] + uvis_mdi[i,j]*mdi[j] - end - end - -#---- sweep downstream to set up BL equations - for i = 2: n # Set up BL loop - simi = xᵢ[i-1] == 0.0 - -#c lami = simi - lami = false - - wake = i > ite - - x = xᵢ[i] - b = bi[i] - rn = rni[i] - th = θᵢ[i] - md = mdi[i] - ue = uₑᵢ[i] - - xm = xᵢ[i-1] - bm = bi[i-1] - rnm = rni[i-1] - thm = θᵢ[i-1] - mdm = mdi[i-1] - uem = uₑᵢ[i-1] - -#c md = ue*ds*(b + 2.0*π*ds*rn) - -#c md/(ue*2*π) = ds*(b/2π + ds*rn) -#c 0.5 rn ds^2 + (b/4π)*ds - md/(4π ue) = 0 -#c ds = ( sqrt(bp^2 + 0.5*md/(π*ue)) - bp ) / rn - bp = b * 0.25/π - mpu = 0.5*md/(π*ue) - if(rn <= 1.0e-6) - ds = md/(ue*b) - ds_md = 1.0/(ue*b) - ds_ue = -ds/ue - else - ds = (sqrt(bp^2 + mpu) - bp) / rn - ds_md = 0.5/sqrt(bp^2 + mpu) * ( mpu/md) / rn - ds_ue = 0.5/sqrt(bp^2 + mpu) * (-mpu/ue) / rn - end - - if(simi) - dsm = 0. - dsm_mdm = 0. - dsm_uem = 0. - else - if(rnm <= 1.0e-6) - dsm = mdm/(uem*bm) - dsm_mdm = 1.0/(uem*bm) - dsm_uem = -dsm/uem - else - bpm = bm * 0.25/π - mpum = 0.5*mdm/(π*uem) - dsm = (sqrt(bpm^2 + mpum) - bpm) / rnm - dsm_mdm = 0.5/sqrt(bpm^2 + mpum) * ( mpum/mdm) / rnm - dsm_uem = 0.5/sqrt(bpm^2 + mpum) * (-mpum/uem) / rnm - end - end - -# if(.not.simi) -# call blvar(simi,lami,wake, Reyn,Mach, fexcr, -# & xm, thm ,dsm ,uem , -# & hm, hm_thm, hm_dsm, -# & hkm, hkm_thm, hkm_dsm, hkm_uem, -# & hcm, hcm_thm, hcm_dsm, hcm_uem, -# & hsm, hsm_thm, hsm_dsm, hsm_uem, -# & cfm, cfm_thm, cfm_dsm, cfm_uem, -# & dim, dim_thm, dim_dsm, dim_uem ) -# end - - (h , ∂h∂θ, ∂h∂δ, - hk, hk_th, hk_ds, hk_ue, - hc, hc_th, hc_ds, hc_ue, - hs, hs_th, hs_ds, hs_ue, - cf, cf_th, cf_ds, cf_ue, - di, di_th, di_ds, di_ue ) = blvar(simi,lami,wake, Reyn,Mach, fexcr,x, th ,ds ,ue) - direct = true - - aa,bb,rr = blsys(simi,lami,wake,direct, Mach, uinv[i],hksep, - x,b,rn,th,ds,ue, - h , ∂h∂θ, ∂h∂δ, - hk, hk_th, hk_ds, hk_ue, - hc, hc_th, hc_ds, hc_ue, - hs, hs_th, hs_ds, hs_ue, - cf, cf_th, cf_ds, cf_ue, - di, di_th, di_ds, di_ue, - xm,bm,rnm,thm,dsm,uem, - hm , hm_thm, hm_dsm, - hkm, hkm_thm, hkm_dsm, hkm_uem, - hcm, hcm_thm, hcm_dsm, hcm_uem, - hsm, hsm_thm, hsm_dsm, hsm_uem, - cfm, cfm_thm, cfm_dsm, cfm_uem, - dim, dim_thm, dim_dsm, dim_uem) - -#------ put BL equations of small 3x3 system into big system - for k = 1: 2 - ksys = 3*(i-1)+ k - rsys[ksys] = rr[k] - - r_th = aa[k,1] - r_ds = aa[k,2] - r_ue = aa[k,3] - - r_thm = bb[k,1] - r_dsm = bb[k,2] - r_uem = bb[k,3] - - lsys = 3*(i-1) + 1 - asys[ksys,lsys ] = r_th - asys[ksys,lsys-3] = r_thm - - lsys = 3*(i-1) + 2 - asys[ksys,lsys ] = r_ds *ds_md - asys[ksys,lsys-3] = r_dsm*dsm_mdm - - lsys = 3*(i-1) + 3 - asys[ksys,lsys ] = r_ds *ds_ue + r_ue - asys[ksys,lsys-3] = r_dsm*dsm_uem + r_uem - end - -#------ set up 3rd ue equation, ue = uvis - k = 3 - ksys = 3*(i-1) + k - rsys[ksys] = ue - uvis[i] - - for j = 1: n - lsys = 3*(j-1) + 2 - asys[ksys,lsys] = -uvis_mdi[i,j] - end - - lsys = 3*(i-1) + 3 - asys[ksys,lsys] = asys[ksys,lsys] + 1.0 - -#------ also store dependent variables for returning - θsᵢ[i] = hs*th - δssᵢ[i] = hc*th - cfi[i] = cf - cdi[i] = di*hs/2.0 - cti[i] = 0.03 * 0.5*hs*((hk-1.0)/hk)^2 - hki[i] = hk - -#------ set dependent i-1 variables for next interval - hm = h - hm_thm = ∂h∂θ - hm_dsm = ∂h∂δ - - hkm = hk - hkm_thm = hk_th - hkm_dsm = hk_ds - hkm_uem = hk_ue - - hsm = hs - hsm_thm = hs_th - hsm_dsm = hs_ds - hsm_uem = hs_ue - - hcm = hc - hcm_thm = hc_th - hcm_dsm = hc_ds - hcm_uem = hc_ue - - if(i>=ite) - cfm = 0. - cfm_thm = 0. - cfm_dsm = 0. - cfm_uem = 0. - else - cfm = cf - cfm_thm = cf_th - cfm_dsm = cf_ds - cfm_uem = cf_ue - end - - dim = di - dim_thm = di_th - dim_dsm = di_ds - dim_uem = di_ue - - end #end BL loop - - -# for i = 1: n -# k1 = 3*[i-1] + 1 -# k2 = 3*[i-1] + 2 -# k3 = 3*[i-1] + 3 -# write(*,'(1x,i4,3e12.4,3x,3g15.7)') -# & i, rsys(k1),rsys(k2),rsys(k3), uₑᵢ[i], uvis[i], uₑᵢ[i]-uvis[i] -# end - -#---- solve Newton system -# call gaussn(kdim,nsys,asys,rsys,1) - -rsys = asys\rsys - -#---- set Newton changes, set max change dmax, and set limiter rlx - dmax = 0. - rlx = 1.0 - for i = 2: n - b = bi[i] - th = θᵢ[i] - md = mdi[i] - ue = uₑᵢ[i] - - kth = 3*(i-1) + 1 - kmd = 3*(i-1) + 2 - kue = 3*(i-1) + 3 - dθᵢ[i] = -rsys[kth] - dmdi[i] = -rsys[kmd] - duₑᵢ[i] = -rsys[kue] - - bp = b * 0.25/π - mpu = 0.5*md/(π*ue) - ds = sqrt(bp^2 + mpu) - bp - ds_md = 0.5/sqrt(bp^2 + mpu) * ( mpu/md) - ds_ue = 0.5/sqrt(bp^2 + mpu) * (-mpu/ue) - -# ds = md/(b*ue) -# ds_md = 1.0/(b*ue) -# ds_ue = -ds/ue - - dδᵢ[i] = ds_md*dmdi[i] + ds_ue*duₑᵢ[i] - - if(rlx*dθᵢ[i] > 1.6*th) rlx = 1.6*th/dθᵢ[i]; end - if(rlx*dθᵢ[i] < -0.6*th) rlx = -0.6*th/dθᵢ[i]; end - if(rlx*dδᵢ[i] > 2.5*ds) rlx = 2.5*ds/dδᵢ[i]; end - if(rlx*dδᵢ[i] < -0.4*ds) rlx = -0.4*ds/dδᵢ[i]; end - if(rlx*duₑᵢ[i] > 0.2*ue) rlx = 0.2*ue/duₑᵢ[i]; end - if(rlx*duₑᵢ[i] < -0.1*ue) rlx = -0.1*ue/duₑᵢ[i]; end - - dmax = max( dmax , abs(dθᵢ[i])/th , - abs(dδᵢ[i])/ds , - abs(duₑᵢ[i])/ue ) - end - -#------ perform Newton updated, with limiter if rlx < 1 - for i = 2: n - θᵢ[i] = θᵢ[i] + rlx*dθᵢ[i] - δᵢ[i] = δᵢ[i] + rlx*dδᵢ[i] - uₑᵢ[i] = uₑᵢ[i] + rlx*duₑᵢ[i] - mdi[i] = uₑᵢ[i]*δᵢ[i]*(bi[i] + 2.0*π*δᵢ[i]*rni[i]) - end - -# for i = 2: n -# θᵢ[i] = θᵢ[i] + rlx*dθᵢ[i] -#cc δᵢ[i] = δᵢ[i] + rlx*dδᵢ[i] -# uₑᵢ[i] = uₑᵢ[i] + rlx*duₑᵢ[i] -# mdi[i] = mdi[i] + rlx*dmdi[i] -# δᵢ[i] = mdi[i]/(bi[i]*uₑᵢ[i]) -# end - -# if(ipass==1) write(*,*) -# write(*,2200) ipass, dmax, rlx -# 2200 format(1x,i4, e12.4, f8.4) - - if(dmax < ε) break; end - - end #End newton iteration - - - -#---- integrate running dissipation - ϕ[1] = 0. - for i = 2: n - x = xᵢ[i] - xm = xᵢ[i-1] - - 𝒟ᵢb = cdi[i] *ρᵢ[i] *uₑᵢ[i]^3 * (bi[i] + 2.0*π*δᵢ[i] *rni[i]) - 𝒟ᵢbm = cdi[i-1]*ρᵢ[i-1]*uₑᵢ[i-1]^3 * (bi[i-1] + 2.0*π*δᵢ[i-1]*rni[i-1]) - - ϕ[i] = ϕ[i-1] + 0.5*(𝒟ᵢb + 𝒟ᵢbm) * (x - xm) - end - - return uₑᵢ, δᵢ, θᵢ, θsᵢ, δssᵢ, cfi, cdi, cti, hki, ϕ - end # blax diff --git a/src/aero/blsys.jl b/src/aero/blsys.jl index 0907f315..8c213421 100644 --- a/src/aero/blsys.jl +++ b/src/aero/blsys.jl @@ -18,7 +18,7 @@ using StaticArrays cfm, cfm_thm, cfm_dsm, cfm_uem, dim, dim_thm, dim_dsm, dim_uem) -Computes Jacobian matrices for BL solution at an axial station. Called repeatedly by [`blax2`](@ref). +Computes Jacobian matrices for BL solution at an axial station. Called repeatedly by [`blax`](@ref). !!! details "🔃 Inputs and Outputs" **Inputs:** diff --git a/src/aero/fusebl.jl b/src/aero/fusebl.jl index b975079f..b0764f7d 100644 --- a/src/aero/fusebl.jl +++ b/src/aero/fusebl.jl @@ -23,7 +23,7 @@ which are defined by the various geometric parameters in `parg`. - No explicit outputs. Computed drag values are saved to `para` of `aircraft` model. See [Simplified Viscous/Inviscid Analysis for Nearly-Axisymmetric Bodies](../assets/drela_TASOPT_2p16/axibl.pdf). -See also [`blax2`](@ref) and [`axisol!`](@ref). +See also [`blax`](@ref) and [`axisol!`](@ref). !!! compat "Future Changes" In an upcoming revision, an `aircraft` struct and auxiliary indices will be passed in lieu of pre-sliced `par` arrays. @@ -137,7 +137,7 @@ function fusebl!(pari, parg, para, ip) fex = para[iafexcdf, ip] uebl, dsbl, thbl, tsbl, dcbl, - cfbl, cdbl, ctbl, hkbl, phbl = blax2(nbldim, nbl,iblte, + cfbl, cdbl, ctbl, hkbl, phbl = blax(nbldim, nbl,iblte, sbl, bbl, rnbl, uinv, Reunit, Mach, fex) gam = 1.4 #gamSL diff --git a/src/air/C.air b/src/airfoil_data/C.air similarity index 100% rename from src/air/C.air rename to src/airfoil_data/C.air diff --git a/src/airfoil_data/Cl.air b/src/airfoil_data/Cl.air new file mode 100644 index 00000000..f524c9fb --- /dev/null +++ b/src/airfoil_data/Cl.air @@ -0,0 +1,1966 @@ + 39 7 7 3 + 0.500000E-01 + 0.100000 + 0.200000 + 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-0.101478 + 0.404964E-02 0.567809E-01 -0.903905E-01 + 0.397657E-02 0.678538E-01 -0.781521E-01 + 0.390407E-02 0.790480E-01 -0.656322E-01 + 0.383000E-02 0.899900E-01 -0.537000E-01 + 0.375277E-02 0.100400 -0.430072E-01 + 0.367296E-02 0.110371 -0.333343E-01 + 0.359166E-02 0.120092 -0.242443E-01 + 0.351000E-02 0.129750 -0.153000E-01 + 0.342889E-02 0.139502 -0.613713E-02 + 0.334852E-02 0.149380 0.331716E-02 + 0.319000E-02 0.169510 0.231000E-01 diff --git a/src/airfoil_data/README b/src/airfoil_data/README new file mode 100644 index 00000000..87854f37 --- /dev/null +++ b/src/airfoil_data/README @@ -0,0 +1,14 @@ +Database files implementing cd(Mach,cl,t/c) functions for families of airfoils. + +C.air +C-series modern transonic airfoils, 9.0% to 14.5% thick. + +Cl.air +C-series with laminar flow on the bottom surface, up to about 60% chord. + +E.air +E-series modern transonic airfoils, 9.0% to 14.5% thick. +Compared to the C-series, the E-series have a deeper aft undercamber. +This gives them a bit higher Mach capability, at the cost of slightly +more drag, more negative cm, larger hinge moment, and a smaller trailing +edge wedge angle. diff --git a/test/unit_test_aero.jl b/test/unit_test_aero.jl index 4c35a867..7c4658d6 100644 --- a/test/unit_test_aero.jl +++ b/test/unit_test_aero.jl @@ -242,7 +242,7 @@ end uei, dsi, thi, tsi, dci, cfi, cdi, cti, - hki, phi = TASOPT.aerodynamics.blax2(nbldim, nbl, iblte, + hki, phi = TASOPT.aerodynamics.blax(nbldim, nbl, iblte, sbl, bbl, rnbl, univ, Reunit, Mach, fex)