From bab9fe9dabb5fc9c03c6a990c034bc4f8653b423 Mon Sep 17 00:00:00 2001 From: faisal-bhuiyan Date: Wed, 2 Oct 2024 13:58:28 -0600 Subject: [PATCH] Transfer unit test files from regression->external directory + add all required input files for the ADI library --- src/utilities/aerodynamics/aerodyn_inflow.hpp | 20 +- tests/unit_tests/CMakeLists.txt | 1 + .../5MW_Baseline/Airfoils/Cylinder1.dat | 59 +++ .../Airfoils/Cylinder1_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/Cylinder2.dat | 60 +++ .../Airfoils/Cylinder2_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/DU21_A17.dat | 196 +++++++++ .../5MW_Baseline/Airfoils/DU21_A17_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/DU25_A17.dat | 194 +++++++++ .../5MW_Baseline/Airfoils/DU25_A17_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/DU30_A17.dat | 198 +++++++++ .../5MW_Baseline/Airfoils/DU30_A17_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/DU35_A17.dat | 189 ++++++++ .../5MW_Baseline/Airfoils/DU35_A17_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/DU40_A17.dat | 190 ++++++++ .../5MW_Baseline/Airfoils/DU40_A17_coords.txt | 407 ++++++++++++++++++ .../5MW_Baseline/Airfoils/NACA64_A17.dat | 181 ++++++++ .../Airfoils/NACA64_A17_coords.txt | 407 ++++++++++++++++++ .../NRELOffshrBsline5MW_AeroDyn_blade.dat | 28 ++ tests/unit_tests/external/CMakeLists.txt | 15 +- tests/unit_tests/external/ad_primary.dat | 185 ++++++++ tests/unit_tests/external/ifw_primary.dat | 71 +++ .../test_aerodyn_inflow.cpp | 20 +- tests/unit_tests/regression/CMakeLists.txt | 1 - 24 files changed, 4831 insertions(+), 33 deletions(-) create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17.dat create mode 100644 tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17_coords.txt create mode 100644 tests/unit_tests/external/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat create mode 100644 tests/unit_tests/external/ad_primary.dat create mode 100644 tests/unit_tests/external/ifw_primary.dat rename tests/unit_tests/{regression => external}/test_aerodyn_inflow.cpp (97%) diff --git a/src/utilities/aerodynamics/aerodyn_inflow.hpp b/src/utilities/aerodynamics/aerodyn_inflow.hpp index 79b719d2..eb6ce0d4 100644 --- a/src/utilities/aerodynamics/aerodyn_inflow.hpp +++ b/src/utilities/aerodynamics/aerodyn_inflow.hpp @@ -561,23 +561,20 @@ class AeroDynInflowLibrary { public: /// Constructor to initialize AeroDyn Inflow library with default settings and optional path AeroDynInflowLibrary( - std::string shared_lib_path = "", ErrorHandling eh = ErrorHandling{}, - FluidProperties fp = FluidProperties{}, + std::string shared_lib_path = "aerodyn_inflow_c_binding.dll", + ErrorHandling eh = ErrorHandling{}, FluidProperties fp = FluidProperties{}, EnvironmentalConditions ec = EnvironmentalConditions{}, TurbineSettings ts = TurbineSettings{}, StructuralMesh sm = StructuralMesh{}, SimulationControls sc = SimulationControls{}, VTKSettings vtk = VTKSettings{} ) - : error_handling_(std::move(eh)), + : lib_{shared_lib_path, util::dylib::no_filename_decorations}, + error_handling_(std::move(eh)), air_(std::move(fp)), env_conditions_(std::move(ec)), turbine_settings_(std::move(ts)), structural_mesh_(std::move(sm)), sim_controls_(std::move(sc)), - vtk_settings_(std::move(vtk)) { - if (!shared_lib_path.empty()) { - lib_ = util::dylib(shared_lib_path, util::dylib::no_filename_decorations); - } - } + vtk_settings_(std::move(vtk)) {} /// Destructor to take care of Fortran-side cleanup if the library is initialized ~AeroDynInflowLibrary() noexcept { @@ -953,11 +950,8 @@ class AeroDynInflowLibrary { } private: - bool is_initialized_{false}; //< Flag to check if the library is initialized - util::dylib lib_{ - "libaerodyn_inflow_c_binding.dylib", - util::dylib::no_filename_decorations //< Dynamic library object for AeroDyn Inflow - }; + bool is_initialized_{false}; //< Flag to check if the library is initialized + util::dylib lib_; //< Dynamic library object for AeroDyn Inflow ErrorHandling error_handling_; //< Error handling settings FluidProperties air_; //< Properties of the working fluid (air) EnvironmentalConditions env_conditions_; //< Environmental conditions diff --git a/tests/unit_tests/CMakeLists.txt b/tests/unit_tests/CMakeLists.txt index 454ffd2c..986e66dc 100644 --- a/tests/unit_tests/CMakeLists.txt +++ b/tests/unit_tests/CMakeLists.txt @@ -3,6 +3,7 @@ add_executable(openturbine_unit_tests) # Add subdirectories for additional components add_subdirectory(beams) +add_subdirectory(external) add_subdirectory(model) add_subdirectory(regression) add_subdirectory(solver) diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1.dat new file mode 100644 index 00000000..d9e59b23 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1.dat @@ -0,0 +1,59 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! Round root section with a Cd of 0.50 +! Made by Jason Jonkman +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"Cylinder1_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + 0 alpha0 ! 0-lift angle of attack, depends on airfoil. + 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + 0 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.5 Cd0 ! 2D drag coefficient value at 0-lift. + 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.5000 0.0 + 0.00 0.000 0.5000 0.0 + 180.00 0.000 0.5000 0.0 +! ------------------------------------------------------------------------------ + diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1_coords.txt new file mode 100644 index 00000000..30663b70 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder1_coords.txt @@ -0,0 +1,407 @@ + 400 NumCoords ! The number of coordinates in the airfoil shape file (including an extra coordinate for airfoil reference). 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-0.082541 +0.996600 -0.058210 +1.000000 0.000000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2.dat new file mode 100644 index 00000000..f6e6a9fe --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2.dat @@ -0,0 +1,60 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! Round root section with a Cd of 0.35 +! Made by Jason Jonkman +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"Cylinder2_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +! ......... x-y coordinates are next if NumCoords > 0 ............. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + 0 alpha0 ! 0-lift angle of attack, depends on airfoil. + 0 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + 0 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + 0 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.35 Cd0 ! 2D drag coefficient value at 0-lift. + 0 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 3 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.3500 0.0 + 0.00 0.000 0.3500 0.0 + 180.00 0.000 0.3500 0.0 +! ------------------------------------------------------------------------------ + diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2_coords.txt new file mode 100644 index 00000000..ba5741b6 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/Cylinder2_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.41667 0 +! coordinates of airfoil shape +! cylinder (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.996600 0.058210 +0.993140 0.082541 +0.989610 0.101400 +0.986010 0.117449 +0.982350 0.131676 +0.978630 0.144614 +0.974840 0.156611 +0.970980 0.167863 +0.967060 0.178480 +0.963070 0.188590 +0.959020 0.198244 +0.954900 0.207523 +0.950720 0.216452 +0.946470 0.225088 +0.942160 0.233441 +0.937780 0.241555 +0.933330 0.249450 +0.928820 0.257125 +0.924250 0.264598 +0.919610 0.271896 +0.914900 0.279030 +0.910130 0.285995 +0.905290 0.292814 +0.900390 0.299479 +0.895420 0.306011 +0.890390 0.312403 +0.885290 0.318672 +0.880130 0.324809 +0.874900 0.330832 +0.869610 0.336732 +0.864250 0.342523 +0.858820 0.348207 +0.853330 0.353777 +0.847780 0.359234 +0.842160 0.364591 +0.836470 0.369849 +0.830720 0.374999 +0.824900 0.380053 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-0.082541 +0.996600 -0.058210 +1.000000 0.000000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17.dat new file mode 100644 index 00000000..9fb97f0d --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17.dat @@ -0,0 +1,196 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU21 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU21_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 8 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -8 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4144 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.5324 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.006 Cd0 ! 2D drag coefficient value at 0-lift. + -0.121 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 142 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0185 0.0000 + -175.00 0.394 0.0332 0.1978 + -170.00 0.788 0.0945 0.3963 + -160.00 0.670 0.2809 0.2738 + -155.00 0.749 0.3932 0.3118 + -150.00 0.797 0.5112 0.3413 + -145.00 0.818 0.6309 0.3636 + -140.00 0.813 0.7485 0.3799 + -135.00 0.786 0.8612 0.3911 + -130.00 0.739 0.9665 0.3980 + -125.00 0.675 1.0625 0.4012 + -120.00 0.596 1.1476 0.4014 + -115.00 0.505 1.2206 0.3990 + -110.00 0.403 1.2805 0.3943 + -105.00 0.294 1.3265 0.3878 + -100.00 0.179 1.3582 0.3796 + -95.00 0.060 1.3752 0.3700 + -90.00 -0.060 1.3774 0.3591 + -85.00 -0.179 1.3648 0.3471 + -80.00 -0.295 1.3376 0.3340 + -75.00 -0.407 1.2962 0.3199 + -70.00 -0.512 1.2409 0.3049 + -65.00 -0.608 1.1725 0.2890 + -60.00 -0.693 1.0919 0.2722 + -55.00 -0.764 1.0002 0.2545 + -50.00 -0.820 0.8990 0.2359 + -45.00 -0.857 0.7900 0.2163 + -40.00 -0.875 0.6754 0.1958 + -35.00 -0.869 0.5579 0.1744 + -30.00 -0.838 0.4405 0.1520 + -25.00 -0.791 0.3256 0.1262 + -24.00 -0.794 0.3013 0.1170 + -23.00 -0.805 0.2762 0.1059 + -22.00 -0.821 0.2506 0.0931 + -21.00 -0.843 0.2246 0.0788 + -20.00 -0.869 0.1983 0.0631 + -19.00 -0.899 0.1720 0.0464 + -18.00 -0.931 0.1457 0.0286 + -17.00 -0.964 0.1197 0.0102 + -16.00 -0.999 0.0940 -0.0088 + -15.00 -1.033 0.0689 -0.0281 + -14.50 -1.050 0.0567 -0.0378 + -12.01 -0.953 0.0271 -0.0349 + -11.00 -0.900 0.0303 -0.0361 + -9.98 -0.827 0.0287 -0.0464 + -8.12 -0.536 0.0124 -0.0821 + -7.62 -0.467 0.0109 -0.0924 + -7.11 -0.393 0.0092 -0.1015 + -6.60 -0.323 0.0083 -0.1073 + -6.50 -0.311 0.0089 -0.1083 + -6.00 -0.245 0.0082 -0.1112 + -5.50 -0.178 0.0074 -0.1146 + -5.00 -0.113 0.0069 -0.1172 + -4.50 -0.048 0.0065 -0.1194 + -4.00 0.016 0.0063 -0.1213 + -3.50 0.080 0.0061 -0.1232 + -3.00 0.145 0.0058 -0.1252 + -2.50 0.208 0.0057 -0.1268 + -2.00 0.270 0.0057 -0.1282 + -1.50 0.333 0.0057 -0.1297 + -1.00 0.396 0.0057 -0.1310 + -0.50 0.458 0.0057 -0.1324 + 0.00 0.521 0.0057 -0.1337 + 0.50 0.583 0.0057 -0.1350 + 1.00 0.645 0.0058 -0.1363 + 1.50 0.706 0.0058 -0.1374 + 2.00 0.768 0.0059 -0.1385 + 2.50 0.828 0.0061 -0.1395 + 3.00 0.888 0.0063 -0.1403 + 3.50 0.948 0.0066 -0.1406 + 4.00 0.996 0.0071 -0.1398 + 4.50 1.046 0.0079 -0.1390 + 5.00 1.095 0.0090 -0.1378 + 5.50 1.145 0.0103 -0.1369 + 6.00 1.192 0.0113 -0.1353 + 6.50 1.239 0.0122 -0.1338 + 7.00 1.283 0.0131 -0.1317 + 7.50 1.324 0.0139 -0.1291 + 8.00 1.358 0.0147 -0.1249 + 8.50 1.385 0.0158 -0.1213 + 9.00 1.403 0.0181 -0.1177 + 9.50 1.401 0.0211 -0.1142 + 10.00 1.358 0.0255 -0.1103 + 10.50 1.313 0.0301 -0.1066 + 11.00 1.287 0.0347 -0.1032 + 11.50 1.274 0.0401 -0.1002 + 12.00 1.272 0.0468 -0.0971 + 12.50 1.273 0.0545 -0.0940 + 13.00 1.273 0.0633 -0.0909 + 13.50 1.273 0.0722 -0.0883 + 14.00 1.272 0.0806 -0.0865 + 14.50 1.273 0.0900 -0.0854 + 15.00 1.275 0.0987 -0.0849 + 15.50 1.281 0.1075 -0.0847 + 16.00 1.284 0.1170 -0.0850 + 16.50 1.296 0.1270 -0.0858 + 17.00 1.306 0.1368 -0.0869 + 17.50 1.308 0.1464 -0.0883 + 18.00 1.308 0.1562 -0.0901 + 18.50 1.308 0.1664 -0.0922 + 19.00 1.308 0.1770 -0.0949 + 19.50 1.307 0.1878 -0.0980 + 20.00 1.311 0.1987 -0.1017 + 20.50 1.325 0.2100 -0.1059 + 21.00 1.324 0.2214 -0.1105 + 22.00 1.277 0.2499 -0.1172 + 23.00 1.229 0.2786 -0.1239 + 24.00 1.182 0.3077 -0.1305 + 25.00 1.136 0.3371 -0.1370 + 26.00 1.093 0.3664 -0.1433 + 28.00 1.017 0.4246 -0.1556 + 30.00 0.962 0.4813 -0.1671 + 32.00 0.937 0.5356 -0.1778 + 35.00 0.947 0.6127 -0.1923 + 40.00 0.950 0.7396 -0.2154 + 45.00 0.928 0.8623 -0.2374 + 50.00 0.884 0.9781 -0.2583 + 55.00 0.821 1.0846 -0.2782 + 60.00 0.740 1.1796 -0.2971 + 65.00 0.646 1.2617 -0.3149 + 70.00 0.540 1.3297 -0.3318 + 75.00 0.425 1.3827 -0.3476 + 80.00 0.304 1.4202 -0.3625 + 85.00 0.179 1.4423 -0.3763 + 90.00 0.053 1.4512 -0.3890 + 95.00 -0.073 1.4480 -0.4004 + 100.00 -0.198 1.4294 -0.4105 + 105.00 -0.319 1.3954 -0.4191 + 110.00 -0.434 1.3464 -0.4260 + 115.00 -0.541 1.2829 -0.4308 + 120.00 -0.637 1.2057 -0.4333 + 125.00 -0.720 1.1157 -0.4330 + 130.00 -0.787 1.0144 -0.4294 + 135.00 -0.836 0.9033 -0.4219 + 140.00 -0.864 0.7845 -0.4098 + 145.00 -0.869 0.6605 -0.3922 + 150.00 -0.847 0.5346 -0.3682 + 155.00 -0.795 0.4103 -0.3364 + 160.00 -0.711 0.2922 -0.2954 + 170.00 -0.788 0.0969 -0.3966 + 175.00 -0.394 0.0334 -0.1978 + 180.00 0.000 0.0185 0.0000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17_coords.txt new file mode 100644 index 00000000..72e36bf8 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU21_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 93-W-210.lm +! x/c y/c +1.00000 0.00194 +0.99660 0.00304 +0.99314 0.00411 +0.98961 0.00516 +0.98601 0.00618 +0.98235 0.00720 +0.97863 0.00823 +0.97484 0.00927 +0.97098 0.01033 +0.96706 0.01139 +0.96307 0.01246 +0.95902 0.01354 +0.95490 0.01463 +0.95072 0.01573 +0.94647 0.01684 +0.94216 0.01797 +0.93778 0.01911 +0.93333 0.02026 +0.92882 0.02142 +0.92425 0.02260 +0.91961 0.02379 +0.91490 0.02499 +0.91013 0.02621 +0.90529 0.02744 +0.90039 0.02869 +0.89542 0.02995 +0.89039 0.03122 +0.88529 0.03250 +0.88013 0.03379 +0.87490 0.03510 +0.86961 0.03643 +0.86425 0.03776 +0.85882 0.03912 +0.85333 0.04048 +0.84778 0.04186 +0.84216 0.04326 +0.83647 0.04466 +0.83072 0.04608 +0.82490 0.04752 +0.81902 0.04896 +0.81307 0.05041 +0.80706 0.05188 +0.80098 0.05336 +0.79484 0.05484 +0.78863 0.05634 +0.78235 0.05784 +0.77601 0.05936 +0.76961 0.06088 +0.76314 0.06242 +0.75660 0.06396 +0.75000 0.06550 +0.74333 0.06706 +0.73667 0.06860 +0.73000 0.07014 +0.72333 0.07167 +0.71667 0.07320 +0.71000 0.07472 +0.70333 0.07624 +0.69667 0.07774 +0.69000 0.07924 +0.68333 0.08072 +0.67667 0.08220 +0.67000 0.08366 +0.66333 0.08511 +0.65667 0.08655 +0.65000 0.08798 +0.64333 0.08940 +0.63667 0.09080 +0.63000 0.09220 +0.62333 0.09357 +0.61667 0.09492 +0.61000 0.09626 +0.60333 0.09759 +0.59667 0.09889 +0.59000 0.10017 +0.58333 0.10143 +0.57667 0.10267 +0.57000 0.10389 +0.56333 0.10509 +0.55667 0.10627 +0.55000 0.10742 +0.54333 0.10854 +0.53667 0.10964 +0.53000 0.11071 +0.52333 0.11175 +0.51667 0.11277 +0.51000 0.11375 +0.50333 0.11470 +0.49667 0.11562 +0.49000 0.11650 +0.48333 0.11734 +0.47667 0.11813 +0.47000 0.11889 +0.46333 0.11960 +0.45667 0.12027 +0.45000 0.12089 +0.44333 0.12147 +0.43667 0.12200 +0.43000 0.12249 +0.42333 0.12292 +0.41667 0.12331 +0.41000 0.12365 +0.40333 0.12394 +0.39667 0.12418 +0.39000 0.12436 +0.38333 0.12449 +0.37667 0.12457 +0.37000 0.12459 +0.36333 0.12455 +0.35667 0.12446 +0.35000 0.12431 +0.34333 0.12411 +0.33667 0.12385 +0.33000 0.12353 +0.32333 0.12317 +0.31667 0.12275 +0.31000 0.12228 +0.30333 0.12175 +0.29667 0.12117 +0.29000 0.12053 +0.28333 0.11984 +0.27667 0.11910 +0.27000 0.11829 +0.26333 0.11744 +0.25667 0.11653 +0.25000 0.11557 +0.24342 0.11456 +0.23693 0.11351 +0.23053 0.11243 +0.22421 0.11130 +0.21798 0.11015 +0.21184 0.10896 +0.20579 0.10773 +0.19982 0.10648 +0.19395 0.10520 +0.18816 0.10389 +0.18245 0.10255 +0.17684 0.10119 +0.17131 0.09980 +0.16587 0.09839 +0.16052 0.09696 +0.15526 0.09550 +0.15008 0.09403 +0.14499 0.09254 +0.13999 0.09103 +0.13508 0.08950 +0.13026 0.08796 +0.12552 0.08641 +0.12087 0.08483 +0.11631 0.08325 +0.11183 0.08165 +0.10745 0.08004 +0.10315 0.07843 +0.09893 0.07679 +0.09481 0.07516 +0.09077 0.07351 +0.08683 0.07186 +0.08297 0.07021 +0.07919 0.06854 +0.07551 0.06687 +0.07191 0.06520 +0.06840 0.06353 +0.06498 0.06185 +0.06164 0.06017 +0.05840 0.05850 +0.05524 0.05682 +0.05217 0.05515 +0.04918 0.05348 +0.04629 0.05181 +0.04348 0.05015 +0.04076 0.04849 +0.03812 0.04683 +0.03558 0.04519 +0.03312 0.04356 +0.03075 0.04194 +0.02847 0.04033 +0.02627 0.03874 +0.02417 0.03716 +0.02215 0.03560 +0.02022 0.03404 +0.01837 0.03249 +0.01662 0.03094 +0.01495 0.02940 +0.01337 0.02785 +0.01187 0.02630 +0.01047 0.02476 +0.00915 0.02322 +0.00792 0.02169 +0.00678 0.02017 +0.00572 0.01864 +0.00476 0.01713 +0.00388 0.01562 +0.00309 0.01410 +0.00238 0.01253 +0.00177 0.01094 +0.00124 0.00923 +0.00080 0.00740 +0.00044 0.00537 +0.00018 0.00333 +0.00000 0.00000 +0.00018 -0.00292 +0.00044 -0.00443 +0.00080 -0.00589 +0.00124 -0.00727 +0.00177 -0.00864 +0.00238 -0.00998 +0.00309 -0.01134 +0.00388 -0.01266 +0.00476 -0.01397 +0.00572 -0.01526 +0.00678 -0.01656 +0.00792 -0.01785 +0.00915 -0.01914 +0.01047 -0.02044 +0.01187 -0.02174 +0.01337 -0.02306 +0.01495 -0.02438 +0.01662 -0.02571 +0.01837 -0.02705 +0.02022 -0.02841 +0.02215 -0.02976 +0.02417 -0.03112 +0.02627 -0.03248 +0.02847 -0.03384 +0.03075 -0.03520 +0.03312 -0.03655 +0.03558 -0.03789 +0.03812 -0.03923 +0.04076 -0.04056 +0.04348 -0.04188 +0.04629 -0.04319 +0.04918 -0.04449 +0.05217 -0.04579 +0.05524 -0.04708 +0.05840 -0.04836 +0.06164 -0.04963 +0.06498 -0.05089 +0.06840 -0.05215 +0.07191 -0.05340 +0.07551 -0.05464 +0.07919 -0.05587 +0.08297 -0.05709 +0.08683 -0.05831 +0.09077 -0.05951 +0.09481 -0.06071 +0.09893 -0.06189 +0.10315 -0.06306 +0.10745 -0.06422 +0.11183 -0.06536 +0.11631 -0.06648 +0.12087 -0.06759 +0.12552 -0.06868 +0.13026 -0.06975 +0.13508 -0.07079 +0.13999 -0.07182 +0.14499 -0.07282 +0.15008 -0.07380 +0.15526 -0.07476 +0.16052 -0.07568 +0.16587 -0.07658 +0.17131 -0.07746 +0.17684 -0.07830 +0.18245 -0.07911 +0.18816 -0.07989 +0.19395 -0.08063 +0.19982 -0.08134 +0.20579 -0.08201 +0.21184 -0.08264 +0.21798 -0.08324 +0.22421 -0.08380 +0.23053 -0.08432 +0.23693 -0.08479 +0.24342 -0.08523 +0.25000 -0.08561 +0.25667 -0.08595 +0.26333 -0.08624 +0.27000 -0.08648 +0.27667 -0.08667 +0.28333 -0.08680 +0.29000 -0.08689 +0.29667 -0.08693 +0.30333 -0.08692 +0.31000 -0.08686 +0.31667 -0.08676 +0.32333 -0.08660 +0.33000 -0.08640 +0.33667 -0.08615 +0.34333 -0.08586 +0.35000 -0.08553 +0.35667 -0.08515 +0.36333 -0.08473 +0.37000 -0.08427 +0.37667 -0.08376 +0.38333 -0.08322 +0.39000 -0.08263 +0.39667 -0.08200 +0.40333 -0.08134 +0.41000 -0.08062 +0.41667 -0.07987 +0.42333 -0.07908 +0.43000 -0.07824 +0.43667 -0.07736 +0.44333 -0.07644 +0.45000 -0.07548 +0.45667 -0.07448 +0.46333 -0.07343 +0.47000 -0.07235 +0.47667 -0.07122 +0.48333 -0.07006 +0.49000 -0.06886 +0.49667 -0.06763 +0.50333 -0.06636 +0.51000 -0.06506 +0.51667 -0.06373 +0.52333 -0.06237 +0.53000 -0.06097 +0.53667 -0.05955 +0.54333 -0.05810 +0.55000 -0.05663 +0.55667 -0.05513 +0.56333 -0.05361 +0.57000 -0.05207 +0.57667 -0.05050 +0.58333 -0.04892 +0.59000 -0.04732 +0.59667 -0.04571 +0.60333 -0.04408 +0.61000 -0.04243 +0.61667 -0.04078 +0.62333 -0.03911 +0.63000 -0.03744 +0.63667 -0.03576 +0.64333 -0.03409 +0.65000 -0.03241 +0.65667 -0.03073 +0.66333 -0.02906 +0.67000 -0.02740 +0.67667 -0.02574 +0.68333 -0.02411 +0.69000 -0.02248 +0.69667 -0.02088 +0.70333 -0.01930 +0.71000 -0.01774 +0.71667 -0.01620 +0.72333 -0.01470 +0.73000 -0.01323 +0.73667 -0.01179 +0.74333 -0.01039 +0.75000 -0.00903 +0.75660 -0.00772 +0.76314 -0.00647 +0.76961 -0.00528 +0.77601 -0.00416 +0.78235 -0.00308 +0.78863 -0.00207 +0.79484 -0.00112 +0.80098 -0.00023 +0.80706 0.00060 +0.81307 0.00136 +0.81902 0.00207 +0.82490 0.00273 +0.83072 0.00333 +0.83647 0.00387 +0.84216 0.00435 +0.84778 0.00479 +0.85333 0.00517 +0.85882 0.00550 +0.86425 0.00578 +0.86961 0.00601 +0.87490 0.00620 +0.88013 0.00633 +0.88529 0.00643 +0.89039 0.00648 +0.89542 0.00649 +0.90039 0.00646 +0.90529 0.00639 +0.91013 0.00628 +0.91490 0.00613 +0.91961 0.00595 +0.92425 0.00574 +0.92882 0.00550 +0.93333 0.00523 +0.93778 0.00494 +0.94216 0.00462 +0.94647 0.00428 +0.95072 0.00392 +0.95490 0.00355 +0.95902 0.00315 +0.96307 0.00275 +0.96706 0.00233 +0.97098 0.00189 +0.97484 0.00145 +0.97863 0.00099 +0.98235 0.00053 +0.98601 0.00005 +0.98961 -0.00044 +0.99314 -0.00094 +0.99660 -0.00143 +1.00000 -0.00194 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17.dat new file mode 100644 index 00000000..60730d0a --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17.dat @@ -0,0 +1,194 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU25 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU25_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 8.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -8.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4336 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.6873 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.006 Cd0 ! 2D drag coefficient value at 0-lift. + -0.12 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 140 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0202 0.0000 + -175.00 0.368 0.0324 0.1845 + -170.00 0.735 0.0943 0.3701 + -160.00 0.695 0.2848 0.2679 + -155.00 0.777 0.4001 0.3046 + -150.00 0.828 0.5215 0.3329 + -145.00 0.850 0.6447 0.3540 + -140.00 0.846 0.7660 0.3693 + -135.00 0.818 0.8823 0.3794 + -130.00 0.771 0.9911 0.3854 + -125.00 0.705 1.0905 0.3878 + -120.00 0.624 1.1787 0.3872 + -115.00 0.530 1.2545 0.3841 + -110.00 0.426 1.3168 0.3788 + -105.00 0.314 1.3650 0.3716 + -100.00 0.195 1.3984 0.3629 + -95.00 0.073 1.4169 0.3529 + -90.00 -0.050 1.4201 0.3416 + -85.00 -0.173 1.4081 0.3292 + -80.00 -0.294 1.3811 0.3159 + -75.00 -0.409 1.3394 0.3017 + -70.00 -0.518 1.2833 0.2866 + -65.00 -0.617 1.2138 0.2707 + -60.00 -0.706 1.1315 0.2539 + -55.00 -0.780 1.0378 0.2364 + -50.00 -0.839 0.9341 0.2181 + -45.00 -0.879 0.8221 0.1991 + -40.00 -0.898 0.7042 0.1792 + -35.00 -0.893 0.5829 0.1587 + -30.00 -0.862 0.4616 0.1374 + -25.00 -0.803 0.3441 0.1154 + -24.00 -0.792 0.3209 0.1101 + -23.00 -0.789 0.2972 0.1031 + -22.00 -0.792 0.2730 0.0947 + -21.00 -0.801 0.2485 0.0849 + -20.00 -0.815 0.2237 0.0739 + -19.00 -0.833 0.1990 0.0618 + -18.00 -0.854 0.1743 0.0488 + -17.00 -0.879 0.1498 0.0351 + -16.00 -0.905 0.1256 0.0208 + -15.00 -0.932 0.1020 0.0060 + -14.00 -0.959 0.0789 -0.0091 + -13.00 -0.985 0.0567 -0.0243 + -12.01 -0.953 0.0271 -0.0349 + -11.00 -0.900 0.0303 -0.0361 + -9.98 -0.827 0.0287 -0.0464 + -8.98 -0.753 0.0271 -0.0534 + -8.47 -0.691 0.0264 -0.0650 + -7.45 -0.555 0.0114 -0.0782 + -6.42 -0.413 0.0094 -0.0904 + -5.40 -0.271 0.0086 -0.1006 + -5.00 -0.220 0.0073 -0.1107 + -4.50 -0.152 0.0071 -0.1135 + -4.00 -0.084 0.0070 -0.1162 + -3.50 -0.018 0.0069 -0.1186 + -3.00 0.049 0.0068 -0.1209 + -2.50 0.115 0.0068 -0.1231 + -2.00 0.181 0.0068 -0.1252 + -1.50 0.247 0.0067 -0.1272 + -1.00 0.312 0.0067 -0.1293 + -0.50 0.377 0.0067 -0.1311 + 0.00 0.444 0.0065 -0.1330 + 0.50 0.508 0.0065 -0.1347 + 1.00 0.573 0.0066 -0.1364 + 1.50 0.636 0.0067 -0.1380 + 2.00 0.701 0.0068 -0.1396 + 2.50 0.765 0.0069 -0.1411 + 3.00 0.827 0.0070 -0.1424 + 3.50 0.890 0.0071 -0.1437 + 4.00 0.952 0.0073 -0.1448 + 4.50 1.013 0.0076 -0.1456 + 5.00 1.062 0.0079 -0.1445 + 6.00 1.161 0.0099 -0.1419 + 6.50 1.208 0.0117 -0.1403 + 7.00 1.254 0.0132 -0.1382 + 7.50 1.301 0.0143 -0.1362 + 8.00 1.336 0.0153 -0.1320 + 8.50 1.369 0.0165 -0.1276 + 9.00 1.400 0.0181 -0.1234 + 9.50 1.428 0.0211 -0.1193 + 10.00 1.442 0.0262 -0.1152 + 10.50 1.427 0.0336 -0.1115 + 11.00 1.374 0.0420 -0.1081 + 11.50 1.316 0.0515 -0.1052 + 12.00 1.277 0.0601 -0.1026 + 12.50 1.250 0.0693 -0.1000 + 13.00 1.246 0.0785 -0.0980 + 13.50 1.247 0.0888 -0.0969 + 14.00 1.256 0.1000 -0.0968 + 14.50 1.260 0.1108 -0.0973 + 15.00 1.271 0.1219 -0.0981 + 15.50 1.281 0.1325 -0.0992 + 16.00 1.289 0.1433 -0.1006 + 16.50 1.294 0.1541 -0.1023 + 17.00 1.304 0.1649 -0.1042 + 17.50 1.309 0.1754 -0.1064 + 18.00 1.315 0.1845 -0.1082 + 18.50 1.320 0.1953 -0.1110 + 19.00 1.330 0.2061 -0.1143 + 19.50 1.343 0.2170 -0.1179 + 20.00 1.354 0.2280 -0.1219 + 20.50 1.359 0.2390 -0.1261 + 21.00 1.360 0.2536 -0.1303 + 22.00 1.325 0.2814 -0.1375 + 23.00 1.288 0.3098 -0.1446 + 24.00 1.251 0.3386 -0.1515 + 25.00 1.215 0.3678 -0.1584 + 26.00 1.181 0.3972 -0.1651 + 28.00 1.120 0.4563 -0.1781 + 30.00 1.076 0.5149 -0.1904 + 32.00 1.056 0.5720 -0.2017 + 35.00 1.066 0.6548 -0.2173 + 40.00 1.064 0.7901 -0.2418 + 45.00 1.035 0.9190 -0.2650 + 50.00 0.980 1.0378 -0.2867 + 55.00 0.904 1.1434 -0.3072 + 60.00 0.810 1.2333 -0.3265 + 65.00 0.702 1.3055 -0.3446 + 70.00 0.582 1.3587 -0.3616 + 75.00 0.456 1.3922 -0.3775 + 80.00 0.326 1.4063 -0.3921 + 85.00 0.197 1.4042 -0.4057 + 90.00 0.072 1.3985 -0.4180 + 95.00 -0.050 1.3973 -0.4289 + 100.00 -0.170 1.3810 -0.4385 + 105.00 -0.287 1.3498 -0.4464 + 110.00 -0.399 1.3041 -0.4524 + 115.00 -0.502 1.2442 -0.4563 + 120.00 -0.596 1.1709 -0.4577 + 125.00 -0.677 1.0852 -0.4563 + 130.00 -0.743 0.9883 -0.4514 + 135.00 -0.792 0.8818 -0.4425 + 140.00 -0.821 0.7676 -0.4288 + 145.00 -0.826 0.6481 -0.4095 + 150.00 -0.806 0.5264 -0.3836 + 155.00 -0.758 0.4060 -0.3497 + 160.00 -0.679 0.2912 -0.3065 + 170.00 -0.735 0.0995 -0.3706 + 175.00 -0.368 0.0356 -0.1846 + 180.00 0.000 0.0202 0.0000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17_coords.txt new file mode 100644 index 00000000..8e481fb8 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU25_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 91-W2-250.lm +! x/c y/c +1.00000 0.00213 +0.99660 0.00314 +0.99314 0.00414 +0.98961 0.00515 +0.98601 0.00617 +0.98235 0.00720 +0.97863 0.00822 +0.97484 0.00926 +0.97098 0.01030 +0.96706 0.01135 +0.96307 0.01240 +0.95902 0.01347 +0.95490 0.01454 +0.95072 0.01562 +0.94647 0.01672 +0.94216 0.01783 +0.93778 0.01895 +0.93333 0.02009 +0.92882 0.02125 +0.92425 0.02241 +0.91961 0.02359 +0.91490 0.02479 +0.91013 0.02600 +0.90529 0.02722 +0.90039 0.02846 +0.89542 0.02972 +0.89039 0.03099 +0.88529 0.03227 +0.88013 0.03357 +0.87490 0.03489 +0.86961 0.03622 +0.86425 0.03756 +0.85882 0.03892 +0.85333 0.04029 +0.84778 0.04167 +0.84216 0.04306 +0.83647 0.04447 +0.83072 0.04589 +0.82490 0.04732 +0.81902 0.04877 +0.81307 0.05023 +0.80706 0.05170 +0.80098 0.05319 +0.79484 0.05468 +0.78863 0.05619 +0.78235 0.05771 +0.77601 0.05925 +0.76961 0.06078 +0.76314 0.06233 +0.75660 0.06388 +0.75000 0.06544 +0.74333 0.06701 +0.73667 0.06857 +0.73000 0.07013 +0.72333 0.07168 +0.71667 0.07322 +0.71000 0.07475 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0.12785 +0.31000 0.12749 +0.30333 0.12705 +0.29667 0.12656 +0.29000 0.12600 +0.28333 0.12538 +0.27667 0.12469 +0.27000 0.12394 +0.26333 0.12312 +0.25667 0.12224 +0.25000 0.12130 +0.24342 0.12030 +0.23693 0.11926 +0.23053 0.11817 +0.22421 0.11704 +0.21798 0.11586 +0.21184 0.11465 +0.20579 0.11340 +0.19982 0.11210 +0.19395 0.11078 +0.18816 0.10942 +0.18245 0.10803 +0.17684 0.10660 +0.17131 0.10515 +0.16587 0.10367 +0.16052 0.10217 +0.15526 0.10064 +0.15008 0.09909 +0.14499 0.09751 +0.13999 0.09591 +0.13508 0.09430 +0.13026 0.09266 +0.12552 0.09101 +0.12087 0.08934 +0.11631 0.08765 +0.11183 0.08595 +0.10745 0.08424 +0.10315 0.08251 +0.09893 0.08076 +0.09481 0.07902 +0.09077 0.07725 +0.08683 0.07549 +0.08297 0.07371 +0.07919 0.07192 +0.07551 0.07013 +0.07191 0.06834 +0.06840 0.06654 +0.06498 0.06474 +0.06164 0.06293 +0.05840 0.06113 +0.05524 0.05933 +0.05217 0.05753 +0.04918 0.05573 +0.04629 0.05393 +0.04348 0.05214 +0.04076 0.05035 +0.03812 0.04856 +0.03558 0.04679 +0.03312 0.04502 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+0.71000 -0.02456 +0.71667 -0.02238 +0.72333 -0.02026 +0.73000 -0.01817 +0.73667 -0.01614 +0.74333 -0.01416 +0.75000 -0.01223 +0.75660 -0.01038 +0.76314 -0.00861 +0.76961 -0.00692 +0.77601 -0.00532 +0.78235 -0.00381 +0.78863 -0.00238 +0.79484 -0.00103 +0.80098 0.00023 +0.80706 0.00141 +0.81307 0.00250 +0.81902 0.00351 +0.82490 0.00444 +0.83072 0.00529 +0.83647 0.00606 +0.84216 0.00675 +0.84778 0.00737 +0.85333 0.00791 +0.85882 0.00839 +0.86425 0.00879 +0.86961 0.00913 +0.87490 0.00940 +0.88013 0.00961 +0.88529 0.00975 +0.89039 0.00983 +0.89542 0.00985 +0.90039 0.00982 +0.90529 0.00972 +0.91013 0.00957 +0.91490 0.00936 +0.91961 0.00910 +0.92425 0.00880 +0.92882 0.00844 +0.93333 0.00804 +0.93778 0.00760 +0.94216 0.00712 +0.94647 0.00660 +0.95072 0.00606 +0.95490 0.00549 +0.95902 0.00490 +0.96307 0.00429 +0.96706 0.00367 +0.97098 0.00303 +0.97484 0.00238 +0.97863 0.00173 +0.98235 0.00108 +0.98601 0.00043 +0.98961 -0.00022 +0.99314 -0.00086 +0.99660 -0.00149 +1.00000 -0.00213 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17.dat new file mode 100644 index 00000000..438015cb --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17.dat @@ -0,0 +1,198 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU30 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU30_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -2.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.449 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.6138 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.008 Cd0 ! 2D drag coefficient value at 0-lift. + -0.09 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 143 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0267 0.0000 + -175.00 0.274 0.0370 0.1379 + -170.00 0.547 0.0968 0.2778 + -160.00 0.685 0.2876 0.2740 + -155.00 0.766 0.4025 0.3118 + -150.00 0.816 0.5232 0.3411 + -145.00 0.836 0.6454 0.3631 + -140.00 0.832 0.7656 0.3791 + -135.00 0.804 0.8807 0.3899 + -130.00 0.756 0.9882 0.3965 + -125.00 0.690 1.0861 0.3994 + -120.00 0.609 1.1730 0.3992 + -115.00 0.515 1.2474 0.3964 + -110.00 0.411 1.3084 0.3915 + -105.00 0.300 1.3552 0.3846 + -100.00 0.182 1.3875 0.3761 + -95.00 0.061 1.4048 0.3663 + -90.00 -0.061 1.4070 0.3551 + -85.00 -0.183 1.3941 0.3428 + -80.00 -0.302 1.3664 0.3295 + -75.00 -0.416 1.3240 0.3153 + -70.00 -0.523 1.2676 0.3001 + -65.00 -0.622 1.1978 0.2841 + -60.00 -0.708 1.1156 0.2672 + -55.00 -0.781 1.0220 0.2494 + -50.00 -0.838 0.9187 0.2308 + -45.00 -0.877 0.8074 0.2113 + -40.00 -0.895 0.6904 0.1909 + -35.00 -0.889 0.5703 0.1696 + -30.00 -0.858 0.4503 0.1475 + -25.00 -0.832 0.3357 0.1224 + -24.00 -0.852 0.3147 0.1156 + -23.00 -0.882 0.2946 0.1081 + -22.00 -0.919 0.2752 0.1000 + -21.00 -0.963 0.2566 0.0914 + -20.00 -1.013 0.2388 0.0823 + -19.00 -1.067 0.2218 0.0728 + -18.00 -1.125 0.2056 0.0631 + -17.00 -1.185 0.1901 0.0531 + -16.00 -1.245 0.1754 0.0430 + -15.25 -1.290 0.1649 0.0353 + -14.24 -1.229 0.1461 0.0240 + -13.24 -1.148 0.1263 0.0100 + -12.22 -1.052 0.1051 -0.0090 + -11.22 -0.965 0.0886 -0.0230 + -10.19 -0.867 0.0740 -0.0336 + -9.70 -0.822 0.0684 -0.0375 + -9.18 -0.769 0.0605 -0.0440 + -8.18 -0.756 0.0270 -0.0578 + -7.19 -0.690 0.0180 -0.0590 + -6.65 -0.616 0.0166 -0.0633 + -6.13 -0.542 0.0152 -0.0674 + -6.00 -0.525 0.0117 -0.0732 + -5.50 -0.451 0.0105 -0.0766 + -5.00 -0.382 0.0097 -0.0797 + -4.50 -0.314 0.0092 -0.0825 + -4.00 -0.251 0.0091 -0.0853 + -3.50 -0.189 0.0089 -0.0884 + -3.00 -0.120 0.0089 -0.0914 + -2.50 -0.051 0.0088 -0.0942 + -2.00 0.017 0.0088 -0.0969 + -1.50 0.085 0.0088 -0.0994 + -1.00 0.152 0.0088 -0.1018 + -0.50 0.219 0.0088 -0.1041 + 0.00 0.288 0.0087 -0.1062 + 0.50 0.354 0.0087 -0.1086 + 1.00 0.421 0.0088 -0.1107 + 1.50 0.487 0.0089 -0.1129 + 2.00 0.554 0.0090 -0.1149 + 2.50 0.619 0.0091 -0.1168 + 3.00 0.685 0.0092 -0.1185 + 3.50 0.749 0.0093 -0.1201 + 4.00 0.815 0.0095 -0.1218 + 4.50 0.879 0.0096 -0.1233 + 5.00 0.944 0.0097 -0.1248 + 5.50 1.008 0.0099 -0.1260 + 6.00 1.072 0.0101 -0.1270 + 6.50 1.135 0.0103 -0.1280 + 7.00 1.197 0.0107 -0.1287 + 7.50 1.256 0.0112 -0.1289 + 8.00 1.305 0.0125 -0.1270 + 9.00 1.390 0.0155 -0.1207 + 9.50 1.424 0.0171 -0.1158 + 10.00 1.458 0.0192 -0.1116 + 10.50 1.488 0.0219 -0.1073 + 11.00 1.512 0.0255 -0.1029 + 11.50 1.533 0.0307 -0.0983 + 12.00 1.549 0.0370 -0.0949 + 12.50 1.558 0.0452 -0.0921 + 13.00 1.470 0.0630 -0.0899 + 13.50 1.398 0.0784 -0.0885 + 14.00 1.354 0.0931 -0.0885 + 14.50 1.336 0.1081 -0.0902 + 15.00 1.333 0.1239 -0.0928 + 15.50 1.326 0.1415 -0.0963 + 16.00 1.329 0.1592 -0.1006 + 16.50 1.326 0.1743 -0.1042 + 17.00 1.321 0.1903 -0.1084 + 17.50 1.331 0.2044 -0.1125 + 18.00 1.333 0.2186 -0.1169 + 18.50 1.340 0.2324 -0.1215 + 19.00 1.362 0.2455 -0.1263 + 19.50 1.382 0.2584 -0.1313 + 20.00 1.398 0.2689 -0.1352 + 20.50 1.426 0.2814 -0.1406 + 21.00 1.437 0.2943 -0.1462 + 22.00 1.418 0.3246 -0.1516 + 23.00 1.397 0.3557 -0.1570 + 24.00 1.376 0.3875 -0.1623 + 25.00 1.354 0.4198 -0.1676 + 26.00 1.332 0.4524 -0.1728 + 28.00 1.293 0.5183 -0.1832 + 30.00 1.265 0.5843 -0.1935 + 32.00 1.253 0.6492 -0.2039 + 35.00 1.264 0.7438 -0.2193 + 40.00 1.258 0.8970 -0.2440 + 45.00 1.217 1.0402 -0.2672 + 50.00 1.146 1.1686 -0.2891 + 55.00 1.049 1.2779 -0.3097 + 60.00 0.932 1.3647 -0.3290 + 65.00 0.799 1.4267 -0.3471 + 70.00 0.657 1.4621 -0.3641 + 75.00 0.509 1.4708 -0.3799 + 80.00 0.362 1.4544 -0.3946 + 85.00 0.221 1.4196 -0.4081 + 90.00 0.092 1.3938 -0.4204 + 95.00 -0.030 1.3943 -0.4313 + 100.00 -0.150 1.3798 -0.4408 + 105.00 -0.267 1.3504 -0.4486 + 110.00 -0.379 1.3063 -0.4546 + 115.00 -0.483 1.2481 -0.4584 + 120.00 -0.578 1.1763 -0.4597 + 125.00 -0.660 1.0919 -0.4582 + 130.00 -0.727 0.9962 -0.4532 + 135.00 -0.777 0.8906 -0.4441 + 140.00 -0.807 0.7771 -0.4303 + 145.00 -0.815 0.6581 -0.4109 + 150.00 -0.797 0.5364 -0.3848 + 155.00 -0.750 0.4157 -0.3508 + 160.00 -0.673 0.3000 -0.3074 + 170.00 -0.547 0.1051 -0.2786 + 175.00 -0.274 0.0388 -0.1380 + 180.00 0.000 0.0267 0.0000 + diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17_coords.txt new file mode 100644 index 00000000..722bf83a --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU30_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! DU 97-W-300.lm +! x/c y/c +1.00000 0.00246 +0.99660 0.00340 +0.99314 0.00437 +0.98961 0.00536 +0.98601 0.00638 +0.98235 0.00740 +0.97863 0.00843 +0.97484 0.00947 +0.97098 0.01051 +0.96706 0.01157 +0.96307 0.01264 +0.95902 0.01371 +0.95490 0.01479 +0.95072 0.01588 +0.94647 0.01698 +0.94216 0.01810 +0.93778 0.01922 +0.93333 0.02036 +0.92882 0.02151 +0.92425 0.02268 +0.91961 0.02386 +0.91490 0.02505 +0.91013 0.02626 +0.90529 0.02749 +0.90039 0.02873 +0.89542 0.02999 +0.89039 0.03126 +0.88529 0.03255 +0.88013 0.03385 +0.87490 0.03516 +0.86961 0.03649 +0.86425 0.03784 +0.85882 0.03921 +0.85333 0.04058 +0.84778 0.04197 +0.84216 0.04337 +0.83647 0.04479 +0.83072 0.04622 +0.82490 0.04767 +0.81902 0.04913 +0.81307 0.05060 +0.80706 0.05208 +0.80098 0.05357 +0.79484 0.05508 +0.78863 0.05659 +0.78235 0.05812 +0.77601 0.05965 +0.76961 0.06120 +0.76314 0.06275 +0.75660 0.06432 +0.75000 0.06589 +0.74333 0.06747 +0.73667 0.06904 +0.73000 0.07061 +0.72333 0.07217 +0.71667 0.07371 +0.71000 0.07525 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0.13420 +0.31000 0.13424 +0.30333 0.13422 +0.29667 0.13415 +0.29000 0.13401 +0.28333 0.13381 +0.27667 0.13355 +0.27000 0.13321 +0.26333 0.13280 +0.25667 0.13231 +0.25000 0.13174 +0.24342 0.13109 +0.23693 0.13036 +0.23053 0.12955 +0.22421 0.12866 +0.21798 0.12771 +0.21184 0.12668 +0.20579 0.12559 +0.19982 0.12444 +0.19395 0.12324 +0.18816 0.12197 +0.18245 0.12066 +0.17684 0.11930 +0.17131 0.11789 +0.16587 0.11644 +0.16052 0.11495 +0.15526 0.11342 +0.15008 0.11185 +0.14499 0.11024 +0.13999 0.10860 +0.13508 0.10693 +0.13026 0.10522 +0.12552 0.10348 +0.12087 0.10172 +0.11631 0.09993 +0.11183 0.09811 +0.10745 0.09627 +0.10315 0.09441 +0.09893 0.09252 +0.09481 0.09061 +0.09077 0.08869 +0.08683 0.08675 +0.08297 0.08478 +0.07919 0.08280 +0.07551 0.08082 +0.07191 0.07881 +0.06840 0.07680 +0.06498 0.07477 +0.06164 0.07274 +0.05840 0.07070 +0.05524 0.06865 +0.05217 0.06660 +0.04918 0.06454 +0.04629 0.06248 +0.04348 0.06042 +0.04076 0.05835 +0.03812 0.05629 +0.03558 0.05423 +0.03312 0.05217 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+0.71000 -0.03931 +0.71667 -0.03703 +0.72333 -0.03478 +0.73000 -0.03256 +0.73667 -0.03037 +0.74333 -0.02822 +0.75000 -0.02610 +0.75660 -0.02405 +0.76314 -0.02205 +0.76961 -0.02013 +0.77601 -0.01827 +0.78235 -0.01647 +0.78863 -0.01474 +0.79484 -0.01309 +0.80098 -0.01150 +0.80706 -0.00998 +0.81307 -0.00854 +0.81902 -0.00717 +0.82490 -0.00586 +0.83072 -0.00462 +0.83647 -0.00346 +0.84216 -0.00236 +0.84778 -0.00133 +0.85333 -0.00037 +0.85882 0.00052 +0.86425 0.00134 +0.86961 0.00210 +0.87490 0.00278 +0.88013 0.00340 +0.88529 0.00395 +0.89039 0.00444 +0.89542 0.00487 +0.90039 0.00524 +0.90529 0.00555 +0.91013 0.00580 +0.91490 0.00600 +0.91961 0.00614 +0.92425 0.00622 +0.92882 0.00625 +0.93333 0.00623 +0.93778 0.00615 +0.94216 0.00602 +0.94647 0.00583 +0.95072 0.00558 +0.95490 0.00528 +0.95902 0.00493 +0.96307 0.00452 +0.96706 0.00405 +0.97098 0.00352 +0.97484 0.00294 +0.97863 0.00231 +0.98235 0.00163 +0.98601 0.00090 +0.98961 0.00012 +0.99314 -0.00071 +0.99660 -0.00158 +1.00000 -0.00246 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17.dat new file mode 100644 index 00000000..48e2b5f3 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17.dat @@ -0,0 +1,189 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU35 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU35_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -1.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 11.5 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -11.5 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.6717 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.3075 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.012 Cd0 ! 2D drag coefficient value at 0-lift. + -0.07 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 135 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0407 0.0000 + -175.00 0.223 0.0507 0.0937 + -170.00 0.405 0.1055 0.1702 + -160.00 0.658 0.2982 0.2819 + -155.00 0.733 0.4121 0.3213 + -150.00 0.778 0.5308 0.3520 + -145.00 0.795 0.6503 0.3754 + -140.00 0.787 0.7672 0.3926 + -135.00 0.757 0.8785 0.4046 + -130.00 0.708 0.9819 0.4121 + -125.00 0.641 1.0756 0.4160 + -120.00 0.560 1.1580 0.4167 + -115.00 0.467 1.2280 0.4146 + -110.00 0.365 1.2847 0.4104 + -105.00 0.255 1.3274 0.4041 + -100.00 0.139 1.3557 0.3961 + -95.00 0.021 1.3692 0.3867 + -90.00 -0.098 1.3680 0.3759 + -85.00 -0.216 1.3521 0.3639 + -80.00 -0.331 1.3218 0.3508 + -75.00 -0.441 1.2773 0.3367 + -70.00 -0.544 1.2193 0.3216 + -65.00 -0.638 1.1486 0.3054 + -60.00 -0.720 1.0660 0.2884 + -55.00 -0.788 0.9728 0.2703 + -50.00 -0.840 0.8705 0.2512 + -45.00 -0.875 0.7611 0.2311 + -40.00 -0.889 0.6466 0.2099 + -35.00 -0.880 0.5299 0.1876 + -30.00 -0.846 0.4141 0.1641 + -25.00 -0.784 0.3030 0.1396 + -24.00 -0.768 0.2817 0.1345 + -23.00 -0.751 0.2608 0.1294 + -22.00 -0.733 0.2404 0.1243 + -21.00 -0.714 0.2205 0.1191 + -20.00 -0.693 0.2011 0.1139 + -19.00 -0.671 0.1822 0.1086 + -18.00 -0.648 0.1640 0.1032 + -17.00 -0.624 0.1465 0.0975 + -16.00 -0.601 0.1300 0.0898 + -15.00 -0.579 0.1145 0.0799 + -14.00 -0.559 0.1000 0.0682 + -13.00 -0.539 0.0867 0.0547 + -12.00 -0.519 0.0744 0.0397 + -11.00 -0.499 0.0633 0.0234 + -10.00 -0.480 0.0534 0.0060 + -5.54 -0.385 0.0245 -0.0800 + -5.04 -0.359 0.0225 -0.0800 + -4.54 -0.360 0.0196 -0.0800 + -4.04 -0.355 0.0174 -0.0800 + -3.54 -0.307 0.0162 -0.0800 + -3.04 -0.246 0.0144 -0.0800 + -3.00 -0.240 0.0240 -0.0623 + -2.50 -0.163 0.0188 -0.0674 + -2.00 -0.091 0.0160 -0.0712 + -1.50 -0.019 0.0137 -0.0746 + -1.00 0.052 0.0118 -0.0778 + -0.50 0.121 0.0104 -0.0806 + 0.00 0.196 0.0094 -0.0831 + 0.50 0.265 0.0096 -0.0863 + 1.00 0.335 0.0098 -0.0895 + 1.50 0.404 0.0099 -0.0924 + 2.00 0.472 0.0100 -0.0949 + 2.50 0.540 0.0102 -0.0973 + 3.00 0.608 0.0103 -0.0996 + 3.50 0.674 0.0104 -0.1016 + 4.00 0.742 0.0105 -0.1037 + 4.50 0.809 0.0107 -0.1057 + 5.00 0.875 0.0108 -0.1076 + 5.50 0.941 0.0109 -0.1094 + 6.00 1.007 0.0110 -0.1109 + 6.50 1.071 0.0113 -0.1118 + 7.00 1.134 0.0115 -0.1127 + 7.50 1.198 0.0117 -0.1138 + 8.00 1.260 0.0120 -0.1144 + 8.50 1.318 0.0126 -0.1137 + 9.00 1.368 0.0133 -0.1112 + 9.50 1.422 0.0143 -0.1100 + 10.00 1.475 0.0156 -0.1086 + 10.50 1.523 0.0174 -0.1064 + 11.00 1.570 0.0194 -0.1044 + 11.50 1.609 0.0227 -0.1013 + 12.00 1.642 0.0269 -0.0980 + 12.50 1.675 0.0319 -0.0953 + 13.00 1.700 0.0398 -0.0925 + 13.50 1.717 0.0488 -0.0896 + 14.00 1.712 0.0614 -0.0864 + 14.50 1.703 0.0786 -0.0840 + 15.50 1.671 0.1173 -0.0830 + 16.00 1.649 0.1377 -0.0848 + 16.50 1.621 0.1600 -0.0880 + 17.00 1.598 0.1814 -0.0926 + 17.50 1.571 0.2042 -0.0984 + 18.00 1.549 0.2316 -0.1052 + 19.00 1.544 0.2719 -0.1158 + 19.50 1.549 0.2906 -0.1213 + 20.00 1.565 0.3085 -0.1248 + 21.00 1.565 0.3447 -0.1317 + 22.00 1.563 0.3820 -0.1385 + 23.00 1.558 0.4203 -0.1452 + 24.00 1.552 0.4593 -0.1518 + 25.00 1.546 0.4988 -0.1583 + 26.00 1.539 0.5387 -0.1647 + 28.00 1.527 0.6187 -0.1770 + 30.00 1.522 0.6978 -0.1886 + 32.00 1.529 0.7747 -0.1994 + 35.00 1.544 0.8869 -0.2148 + 40.00 1.529 1.0671 -0.2392 + 45.00 1.471 1.2319 -0.2622 + 50.00 1.376 1.3747 -0.2839 + 55.00 1.249 1.4899 -0.3043 + 60.00 1.097 1.5728 -0.3236 + 65.00 0.928 1.6202 -0.3417 + 70.00 0.750 1.6302 -0.3586 + 75.00 0.570 1.6031 -0.3745 + 80.00 0.396 1.5423 -0.3892 + 85.00 0.237 1.4598 -0.4028 + 90.00 0.101 1.4041 -0.4151 + 95.00 -0.022 1.4053 -0.4261 + 100.00 -0.143 1.3914 -0.4357 + 105.00 -0.261 1.3625 -0.4437 + 110.00 -0.374 1.3188 -0.4498 + 115.00 -0.480 1.2608 -0.4538 + 120.00 -0.575 1.1891 -0.4553 + 125.00 -0.659 1.1046 -0.4540 + 130.00 -0.727 1.0086 -0.4492 + 135.00 -0.778 0.9025 -0.4405 + 140.00 -0.809 0.7883 -0.4270 + 145.00 -0.818 0.6684 -0.4078 + 150.00 -0.800 0.5457 -0.3821 + 155.00 -0.754 0.4236 -0.3484 + 160.00 -0.677 0.3066 -0.3054 + 170.00 -0.417 0.1085 -0.1842 + 175.00 -0.229 0.0510 -0.1013 + 180.00 0.000 0.0407 0.0000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17_coords.txt new file mode 100644 index 00000000..5d3f84e8 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU35_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! Adjusted DU 35 +! x/c y/c +1.00000 0.00283 +0.99660 0.00378 +0.99314 0.00477 +0.98961 0.00578 +0.98601 0.00683 +0.98235 0.00789 +0.97863 0.00897 +0.97484 0.01006 +0.97098 0.01116 +0.96706 0.01228 +0.96307 0.01342 +0.95902 0.01456 +0.95490 0.01571 +0.95072 0.01688 +0.94647 0.01806 +0.94216 0.01926 +0.93778 0.02046 +0.93333 0.02169 +0.92882 0.02292 +0.92425 0.02419 +0.91961 0.02547 +0.91490 0.02675 +0.91013 0.02807 +0.90529 0.02941 +0.90039 0.03077 +0.89542 0.03214 +0.89039 0.03353 +0.88529 0.03495 +0.88013 0.03638 +0.87490 0.03782 +0.86961 0.03929 +0.86425 0.04079 +0.85882 0.04230 +0.85333 0.04383 +0.84778 0.04538 +0.84216 0.04694 +0.83647 0.04853 +0.83072 0.05013 +0.82490 0.05176 +0.81902 0.05340 +0.81307 0.05506 +0.80706 0.05673 +0.80098 0.05842 +0.79484 0.06013 +0.78863 0.06184 +0.78235 0.06358 +0.77601 0.06531 +0.76961 0.06708 +0.76314 0.06885 +0.75660 0.07064 +0.75000 0.07244 +0.74333 0.07426 +0.73667 0.07606 +0.73000 0.07786 +0.72333 0.07966 +0.71667 0.08144 +0.71000 0.08322 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-0.00283 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17.dat new file mode 100644 index 00000000..54a6d4ac --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17.dat @@ -0,0 +1,190 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! DU40 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"DU40_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -3.2 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.3519 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.3226 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.03 Cd0 ! 2D drag coefficient value at 0-lift. + -0.05 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] + 0.2 x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 136 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0602 0.0000 + -175.00 0.218 0.0699 0.0934 + -170.00 0.397 0.1107 0.1697 + -160.00 0.642 0.3045 0.2813 + -155.00 0.715 0.4179 0.3208 + -150.00 0.757 0.5355 0.3516 + -145.00 0.772 0.6535 0.3752 + -140.00 0.762 0.7685 0.3926 + -135.00 0.731 0.8777 0.4048 + -130.00 0.680 0.9788 0.4126 + -125.00 0.613 1.0700 0.4166 + -120.00 0.532 1.1499 0.4176 + -115.00 0.439 1.2174 0.4158 + -110.00 0.337 1.2716 0.4117 + -105.00 0.228 1.3118 0.4057 + -100.00 0.114 1.3378 0.3979 + -95.00 -0.002 1.3492 0.3887 + -90.00 -0.120 1.3460 0.3781 + -85.00 -0.236 1.3283 0.3663 + -80.00 -0.349 1.2964 0.3534 + -75.00 -0.456 1.2507 0.3394 + -70.00 -0.557 1.1918 0.3244 + -65.00 -0.647 1.1204 0.3084 + -60.00 -0.727 1.0376 0.2914 + -55.00 -0.792 0.9446 0.2733 + -50.00 -0.842 0.8429 0.2543 + -45.00 -0.874 0.7345 0.2342 + -40.00 -0.886 0.6215 0.2129 + -35.00 -0.875 0.5067 0.1906 + -30.00 -0.839 0.3932 0.1670 + -25.00 -0.777 0.2849 0.1422 + -24.00 -0.761 0.2642 0.1371 + -23.00 -0.744 0.2440 0.1320 + -22.00 -0.725 0.2242 0.1268 + -21.00 -0.706 0.2049 0.1215 + -20.00 -0.685 0.1861 0.1162 + -19.00 -0.662 0.1687 0.1097 + -18.00 -0.635 0.1533 0.1012 + -17.00 -0.605 0.1398 0.0907 + -16.00 -0.571 0.1281 0.0784 + -15.00 -0.534 0.1183 0.0646 + -14.00 -0.494 0.1101 0.0494 + -13.00 -0.452 0.1036 0.0330 + -12.00 -0.407 0.0986 0.0156 + -11.00 -0.360 0.0951 -0.0026 + -10.00 -0.311 0.0931 -0.0213 + -8.00 -0.208 0.0930 -0.0600 + -6.00 -0.111 0.0689 -0.0500 + -5.50 -0.090 0.0614 -0.0516 + -5.00 -0.072 0.0547 -0.0532 + -4.50 -0.065 0.0480 -0.0538 + -4.00 -0.054 0.0411 -0.0544 + -3.50 -0.017 0.0349 -0.0554 + -3.00 0.003 0.0299 -0.0558 + -2.50 0.014 0.0255 -0.0555 + -2.00 0.009 0.0198 -0.0534 + -1.50 0.004 0.0164 -0.0442 + -1.00 0.036 0.0147 -0.0469 + -0.50 0.073 0.0137 -0.0522 + 0.00 0.137 0.0113 -0.0573 + 0.50 0.213 0.0114 -0.0644 + 1.00 0.292 0.0118 -0.0718 + 1.50 0.369 0.0122 -0.0783 + 2.00 0.444 0.0124 -0.0835 + 2.50 0.514 0.0124 -0.0866 + 3.00 0.580 0.0123 -0.0887 + 3.50 0.645 0.0120 -0.0900 + 4.00 0.710 0.0119 -0.0914 + 4.50 0.776 0.0122 -0.0933 + 5.00 0.841 0.0125 -0.0947 + 5.50 0.904 0.0129 -0.0957 + 6.00 0.967 0.0135 -0.0967 + 6.50 1.027 0.0144 -0.0973 + 7.00 1.084 0.0158 -0.0972 + 7.50 1.140 0.0174 -0.0972 + 8.00 1.193 0.0198 -0.0968 + 8.50 1.242 0.0231 -0.0958 + 9.00 1.287 0.0275 -0.0948 + 9.50 1.333 0.0323 -0.0942 + 10.00 1.368 0.0393 -0.0926 + 10.50 1.400 0.0475 -0.0908 + 11.00 1.425 0.0580 -0.0890 + 11.50 1.449 0.0691 -0.0877 + 12.00 1.473 0.0816 -0.0870 + 12.50 1.494 0.0973 -0.0870 + 13.00 1.513 0.1129 -0.0876 + 13.50 1.538 0.1288 -0.0886 + 14.50 1.587 0.1650 -0.0917 + 15.00 1.614 0.1845 -0.0939 + 15.50 1.631 0.2052 -0.0966 + 16.00 1.649 0.2250 -0.0996 + 16.50 1.666 0.2467 -0.1031 + 17.00 1.681 0.2684 -0.1069 + 17.50 1.699 0.2900 -0.1110 + 18.00 1.719 0.3121 -0.1157 + 19.00 1.751 0.3554 -0.1242 + 19.50 1.767 0.3783 -0.1291 + 20.50 1.798 0.4212 -0.1384 + 21.00 1.810 0.4415 -0.1416 + 22.00 1.830 0.4830 -0.1479 + 23.00 1.847 0.5257 -0.1542 + 24.00 1.861 0.5694 -0.1603 + 25.00 1.872 0.6141 -0.1664 + 26.00 1.881 0.6593 -0.1724 + 28.00 1.894 0.7513 -0.1841 + 30.00 1.904 0.8441 -0.1954 + 32.00 1.915 0.9364 -0.2063 + 35.00 1.929 1.0722 -0.2220 + 40.00 1.903 1.2873 -0.2468 + 45.00 1.820 1.4796 -0.2701 + 50.00 1.690 1.6401 -0.2921 + 55.00 1.522 1.7609 -0.3127 + 60.00 1.323 1.8360 -0.3321 + 65.00 1.106 1.8614 -0.3502 + 70.00 0.880 1.8347 -0.3672 + 75.00 0.658 1.7567 -0.3830 + 80.00 0.449 1.6334 -0.3977 + 85.00 0.267 1.4847 -0.4112 + 90.00 0.124 1.3879 -0.4234 + 95.00 0.002 1.3912 -0.4343 + 100.00 -0.118 1.3795 -0.4437 + 105.00 -0.235 1.3528 -0.4514 + 110.00 -0.348 1.3114 -0.4573 + 115.00 -0.453 1.2557 -0.4610 + 120.00 -0.549 1.1864 -0.4623 + 125.00 -0.633 1.1041 -0.4606 + 130.00 -0.702 1.0102 -0.4554 + 135.00 -0.754 0.9060 -0.4462 + 140.00 -0.787 0.7935 -0.4323 + 145.00 -0.797 0.6750 -0.4127 + 150.00 -0.782 0.5532 -0.3863 + 155.00 -0.739 0.4318 -0.3521 + 160.00 -0.664 0.3147 -0.3085 + 170.00 -0.410 0.1144 -0.1858 + 175.00 -0.226 0.0702 -0.1022 + 180.00 0.000 0.0602 0.0000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17_coords.txt new file mode 100644 index 00000000..18d11b7b --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/DU40_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.33087 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! Adjusted DU4050 +! x/c y/c +1.00000 0.00347 +0.99660 0.00455 +0.99314 0.00565 +0.98961 0.00678 +0.98601 0.00795 +0.98235 0.00914 +0.97863 0.01035 +0.97484 0.01158 +0.97098 0.01283 +0.96706 0.01410 +0.96307 0.01539 +0.95902 0.01670 +0.95490 0.01803 +0.95072 0.01937 +0.94647 0.02074 +0.94216 0.02212 +0.93778 0.02352 +0.93333 0.02495 +0.92882 0.02639 +0.92425 0.02786 +0.91961 0.02936 +0.91490 0.03087 +0.91013 0.03242 +0.90529 0.03400 +0.90039 0.03560 +0.89542 0.03723 +0.89039 0.03887 +0.88529 0.04056 +0.88013 0.04226 +0.87490 0.04399 +0.86961 0.04575 +0.86425 0.04754 +0.85882 0.04935 +0.85333 0.05119 +0.84778 0.05305 +0.84216 0.05493 +0.83647 0.05685 +0.83072 0.05878 +0.82490 0.06076 +0.81902 0.06275 +0.81307 0.06476 +0.80706 0.06680 +0.80098 0.06886 +0.79484 0.07094 +0.78863 0.07304 +0.78235 0.07517 +0.77601 0.07730 +0.76961 0.07947 +0.76314 0.08165 +0.75660 0.08386 +0.75000 0.08608 +0.74333 0.08832 +0.73667 0.09056 +0.73000 0.09279 +0.72333 0.09502 +0.71667 0.09724 +0.71000 0.09946 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-0.00347 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17.dat b/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17.dat new file mode 100644 index 00000000..b9dca301 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17.dat @@ -0,0 +1,181 @@ +! ------------ AirfoilInfo v1.01.x Input File ---------------------------------- +! NACA64 airfoil with an aspect ratio of 17. Original -180 to 180deg Cl, Cd, and Cm versus AOA data taken from Appendix A of DOWEC document 10046_009.pdf (numerical values obtained from Koert Lindenburg of ECN). +! Cl and Cd values corrected for rotational stall delay and Cd values corrected using the Viterna method for 0 to 90deg AOA by Jason Jonkman using AirfoilPrep_v2p0.xls. +! note that this file uses Marshall Buhl's new input file processing; start all comment lines with ! +! ------------------------------------------------------------------------------ +"DEFAULT" InterpOrd ! Interpolation order to use for quasi-steady table lookup {1=linear; 3=cubic spline; "default"} [default=1] + 1 NonDimArea ! The non-dimensional area of the airfoil (area/chord^2) (set to 1.0 if unsure or unneeded) +@"NACA64_A17_coords.txt" NumCoords ! The number of coordinates in the airfoil shape file. Set to zero if coordinates not included. +"unused" BL_file ! The file name including the boundary layer characteristics of the profile. Ignored if the aeroacoustic module is not called. + 1 NumTabs ! Number of airfoil tables in this file. +! ------------------------------------------------------------------------------ +! data for table 1 +! ------------------------------------------------------------------------------ + 0.75 Re ! Reynolds number in millions + 0 UserProp ! User property (control) setting +True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line +!........................................ + -4.432 alpha0 ! 0-lift angle of attack, depends on airfoil. + 9 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) + -9 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] + 0 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] + 0 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] + 1.4073 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It can be calculated from the static value of Cn at either the break in the pitching moment or the loss of chord force at the onset of stall. It is close to the condition of maximum lift of the airfoil at low Mach numbers. + -0.7945 Cn2 ! As Cn1 for negative AOAs. + 0.19 St_sh ! Strouhal's shedding frequency constant. [default = 0.19] + 0.0065 Cd0 ! 2D drag coefficient value at 0-lift. + -0.088 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does not include a column for Cm, this needs to be set to 0.0] + 0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] + 0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] + 0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] +"Default" x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] +"Default" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] +"DEFAULT" filtCutOff ! Reduced frequency cut-off for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (-) [default = 0.5] +!........................................ +! Table of aerodynamics coefficients + 127 NumAlf ! Number of data lines in the following table +! Alpha Cl Cd Cm +! (deg) (-) (-) (-) + -180.00 0.000 0.0198 0.0000 + -175.00 0.374 0.0341 0.1880 + -170.00 0.749 0.0955 0.3770 + -160.00 0.659 0.2807 0.2747 + -155.00 0.736 0.3919 0.3130 + -150.00 0.783 0.5086 0.3428 + -145.00 0.803 0.6267 0.3654 + -140.00 0.798 0.7427 0.3820 + -135.00 0.771 0.8537 0.3935 + -130.00 0.724 0.9574 0.4007 + -125.00 0.660 1.0519 0.4042 + -120.00 0.581 1.1355 0.4047 + -115.00 0.491 1.2070 0.4025 + -110.00 0.390 1.2656 0.3981 + -105.00 0.282 1.3104 0.3918 + -100.00 0.169 1.3410 0.3838 + -95.00 0.052 1.3572 0.3743 + -90.00 -0.067 1.3587 0.3636 + -85.00 -0.184 1.3456 0.3517 + -80.00 -0.299 1.3181 0.3388 + -75.00 -0.409 1.2765 0.3248 + -70.00 -0.512 1.2212 0.3099 + -65.00 -0.606 1.1532 0.2940 + -60.00 -0.689 1.0731 0.2772 + -55.00 -0.759 0.9822 0.2595 + -50.00 -0.814 0.8820 0.2409 + -45.00 -0.850 0.7742 0.2212 + -40.00 -0.866 0.6610 0.2006 + -35.00 -0.860 0.5451 0.1789 + -30.00 -0.829 0.4295 0.1563 + -25.00 -0.853 0.3071 0.1156 + -24.00 -0.870 0.2814 0.1040 + -23.00 -0.890 0.2556 0.0916 + -22.00 -0.911 0.2297 0.0785 + -21.00 -0.934 0.2040 0.0649 + -20.00 -0.958 0.1785 0.0508 + -19.00 -0.982 0.1534 0.0364 + -18.00 -1.005 0.1288 0.0218 + -17.00 -1.082 0.1037 0.0129 + -16.00 -1.113 0.0786 -0.0028 + -15.00 -1.105 0.0535 -0.0251 + -14.00 -1.078 0.0283 -0.0419 + -13.50 -1.053 0.0158 -0.0521 + -13.00 -1.015 0.0151 -0.0610 + -12.00 -0.904 0.0134 -0.0707 + -11.00 -0.807 0.0121 -0.0722 + -10.00 -0.711 0.0111 -0.0734 + -9.00 -0.595 0.0099 -0.0772 + -8.00 -0.478 0.0091 -0.0807 + -7.00 -0.375 0.0086 -0.0825 + -6.00 -0.264 0.0082 -0.0832 + -5.00 -0.151 0.0079 -0.0841 + -4.00 -0.017 0.0072 -0.0869 + -3.00 0.088 0.0064 -0.0912 + -2.00 0.213 0.0054 -0.0946 + -1.00 0.328 0.0052 -0.0971 + 0.00 0.442 0.0052 -0.1014 + 1.00 0.556 0.0052 -0.1076 + 2.00 0.670 0.0053 -0.1126 + 3.00 0.784 0.0053 -0.1157 + 4.00 0.898 0.0054 -0.1199 + 5.00 1.011 0.0058 -0.1240 + 6.00 1.103 0.0091 -0.1234 + 7.00 1.181 0.0113 -0.1184 + 8.00 1.257 0.0124 -0.1163 + 8.50 1.293 0.0130 -0.1163 + 9.00 1.326 0.0136 -0.1160 + 9.50 1.356 0.0143 -0.1154 + 10.00 1.382 0.0150 -0.1149 + 10.50 1.400 0.0267 -0.1145 + 11.00 1.415 0.0383 -0.1143 + 11.50 1.425 0.0498 -0.1147 + 12.00 1.434 0.0613 -0.1158 + 12.50 1.443 0.0727 -0.1165 + 13.00 1.451 0.0841 -0.1153 + 13.50 1.453 0.0954 -0.1131 + 14.00 1.448 0.1065 -0.1112 + 14.50 1.444 0.1176 -0.1101 + 15.00 1.445 0.1287 -0.1103 + 15.50 1.447 0.1398 -0.1109 + 16.00 1.448 0.1509 -0.1114 + 16.50 1.444 0.1619 -0.1111 + 17.00 1.438 0.1728 -0.1097 + 17.50 1.439 0.1837 -0.1079 + 18.00 1.448 0.1947 -0.1080 + 18.50 1.452 0.2057 -0.1090 + 19.00 1.448 0.2165 -0.1086 + 19.50 1.438 0.2272 -0.1077 + 20.00 1.428 0.2379 -0.1099 + 21.00 1.401 0.2590 -0.1169 + 22.00 1.359 0.2799 -0.1190 + 23.00 1.300 0.3004 -0.1235 + 24.00 1.220 0.3204 -0.1393 + 25.00 1.168 0.3377 -0.1440 + 26.00 1.116 0.3554 -0.1486 + 28.00 1.015 0.3916 -0.1577 + 30.00 0.926 0.4294 -0.1668 + 32.00 0.855 0.4690 -0.1759 + 35.00 0.800 0.5324 -0.1897 + 40.00 0.804 0.6452 -0.2126 + 45.00 0.793 0.7573 -0.2344 + 50.00 0.763 0.8664 -0.2553 + 55.00 0.717 0.9708 -0.2751 + 60.00 0.656 1.0693 -0.2939 + 65.00 0.582 1.1606 -0.3117 + 70.00 0.495 1.2438 -0.3285 + 75.00 0.398 1.3178 -0.3444 + 80.00 0.291 1.3809 -0.3593 + 85.00 0.176 1.4304 -0.3731 + 90.00 0.053 1.4565 -0.3858 + 95.00 -0.074 1.4533 -0.3973 + 100.00 -0.199 1.4345 -0.4075 + 105.00 -0.321 1.4004 -0.4162 + 110.00 -0.436 1.3512 -0.4231 + 115.00 -0.543 1.2874 -0.4280 + 120.00 -0.640 1.2099 -0.4306 + 125.00 -0.723 1.1196 -0.4304 + 130.00 -0.790 1.0179 -0.4270 + 135.00 -0.840 0.9064 -0.4196 + 140.00 -0.868 0.7871 -0.4077 + 145.00 -0.872 0.6627 -0.3903 + 150.00 -0.850 0.5363 -0.3665 + 155.00 -0.798 0.4116 -0.3349 + 160.00 -0.714 0.2931 -0.2942 + 170.00 -0.749 0.0971 -0.3771 + 175.00 -0.374 0.0334 -0.1879 + 180.00 0.000 0.0198 0.0000 diff --git a/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17_coords.txt b/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17_coords.txt new file mode 100644 index 00000000..b2b49e07 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/Airfoils/NACA64_A17_coords.txt @@ -0,0 +1,407 @@ + 400 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 +0.25 0 +! coordinates of airfoil shape; data from TU Delft as posted here: https://wind.nrel.gov/forum/wind/viewtopic.php?f=2&t=440 +! NACA 64-618 (interpolated to 399 points) +! x/c y/c +1.000000 0.000000 +0.990000 0.003385 +0.980000 0.006126 +0.975000 0.007447 +0.970000 0.008767 +0.965000 0.010062 +0.960000 0.011357 +0.955000 0.012639 +0.950000 0.013921 +0.945000 0.015200 +0.940000 0.016478 +0.935000 0.017757 +0.930000 0.019036 +0.925000 0.020317 +0.920000 0.021598 +0.915000 0.022881 +0.910000 0.024163 +0.905000 0.025448 +0.900000 0.026733 +0.887500 0.029951 +0.875000 0.033169 +0.862500 0.036386 +0.850000 0.039603 +0.837500 0.042804 +0.825000 0.046004 +0.812500 0.049171 +0.800000 0.052337 +0.787500 0.055452 +0.775000 0.058566 +0.762500 0.061611 +0.750000 0.064656 +0.737500 0.067615 +0.725000 0.070573 +0.712500 0.073429 +0.700000 0.076285 +0.687500 0.079029 +0.675000 0.081773 +0.662500 0.084393 +0.650000 0.087012 +0.637500 0.089490 +0.625000 0.091967 +0.612500 0.094283 +0.600000 0.096599 +0.587500 0.098743 +0.575000 0.100887 +0.562500 0.102843 +0.550000 0.104799 +0.537500 0.106549 +0.525000 0.108299 +0.512500 0.109830 +0.500000 0.111360 +0.487500 0.112649 +0.475000 0.113937 +0.462500 0.114964 +0.450000 0.115990 +0.445000 0.116320 +0.440000 0.116650 +0.435000 0.116931 +0.430000 0.117211 +0.425000 0.117439 +0.420000 0.117667 +0.415000 0.117835 +0.410000 0.118003 +0.405000 0.118104 +0.400000 0.118204 +0.395000 0.118231 +0.390000 0.118258 +0.385000 0.118213 +0.380000 0.118168 +0.375000 0.118057 +0.370000 0.117946 +0.365000 0.117777 +0.360000 0.117607 +0.355000 0.117383 +0.350000 0.117159 +0.345000 0.116881 +0.340000 0.116603 +0.335000 0.116273 +0.330000 0.115942 +0.325000 0.115562 +0.320000 0.115181 +0.315000 0.114750 +0.310000 0.114319 +0.305000 0.113838 +0.300000 0.113356 +0.295000 0.112824 +0.290000 0.112292 +0.285000 0.111710 +0.280000 0.111127 +0.275000 0.110495 +0.270000 0.109863 +0.265000 0.109180 +0.260000 0.108497 +0.255000 0.107762 +0.250000 0.107027 +0.245000 0.106241 +0.240000 0.105454 +0.235000 0.104614 +0.230000 0.103774 +0.225000 0.102880 +0.220000 0.101985 +0.215000 0.101035 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-0.061163 +0.265000 -0.061354 +0.270000 -0.061545 +0.275000 -0.061708 +0.280000 -0.061871 +0.285000 -0.062004 +0.290000 -0.062137 +0.295000 -0.062240 +0.300000 -0.062343 +0.305000 -0.062417 +0.310000 -0.062490 +0.315000 -0.062534 +0.320000 -0.062577 +0.325000 -0.062590 +0.330000 -0.062602 +0.335000 -0.062583 +0.340000 -0.062563 +0.345000 -0.062512 +0.350000 -0.062460 +0.355000 -0.062374 +0.360000 -0.062287 +0.365000 -0.062164 +0.370000 -0.062040 +0.375000 -0.061878 +0.380000 -0.061716 +0.385000 -0.061509 +0.390000 -0.061301 +0.395000 -0.061040 +0.400000 -0.060778 +0.405000 -0.060458 +0.410000 -0.060138 +0.415000 -0.059763 +0.420000 -0.059388 +0.425000 -0.058966 +0.430000 -0.058544 +0.435000 -0.058083 +0.440000 -0.057622 +0.445000 -0.057127 +0.450000 -0.056632 +0.462500 -0.055265 +0.475000 -0.053897 +0.487500 -0.052374 +0.500000 -0.050850 +0.512500 -0.049195 +0.525000 -0.047539 +0.537500 -0.045777 +0.550000 -0.044014 +0.562500 -0.042165 +0.575000 -0.040316 +0.587500 -0.038401 +0.600000 -0.036486 +0.612500 -0.034526 +0.625000 -0.032565 +0.637500 -0.030575 +0.650000 -0.028585 +0.662500 -0.026594 +0.675000 -0.024603 +0.687500 -0.022632 +0.700000 -0.020660 +0.712500 -0.018728 +0.725000 -0.016795 +0.737500 -0.014922 +0.750000 -0.013048 +0.762500 -0.011260 +0.775000 -0.009472 +0.787500 -0.007797 +0.800000 -0.006122 +0.812500 -0.004594 +0.825000 -0.003065 +0.837500 -0.001721 +0.850000 -0.000376 +0.862500 0.000742 +0.875000 0.001859 +0.887500 0.002698 +0.900000 0.003536 +0.905000 0.003780 +0.910000 0.004023 +0.915000 0.004205 +0.920000 0.004387 +0.925000 0.004504 +0.930000 0.004620 +0.935000 0.004661 +0.940000 0.004702 +0.945000 0.004658 +0.950000 0.004614 +0.955000 0.004476 +0.960000 0.004338 +0.965000 0.004084 +0.970000 0.003829 +0.975000 0.003436 +0.980000 0.003042 +0.990000 0.001910 +1.000000 0.000000 diff --git a/tests/unit_tests/external/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat b/tests/unit_tests/external/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat new file mode 100644 index 00000000..afef3475 --- /dev/null +++ b/tests/unit_tests/external/5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat @@ -0,0 +1,28 @@ +------- AERODYN v15.00.* BLADE DEFINITION INPUT FILE ------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic blade input properties; note that we need to add the aerodynamic center to this file +====== Blade Properties ================================================================= + 19 NumBlNds - Number of blade nodes used in the analysis (-) + BlSpn BlCrvAC BlSwpAC BlCrvAng BlTwist BlChord BlAFID BlCb BlCenBn BlCenBt + (m) (m) (m) (deg) (deg) (m) (-) (-) (m) (m) +0.0000000E+00 0.0000000E+00 0.0000000E+00 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0 +1.3667000E+00 -8.1531745E-04 -3.4468858E-03 0.0000000E+00 1.3308000E+01 3.5420000E+00 1 0.0 0.0 0.0 +4.1000000E+00 -2.4839790E-02 -1.0501421E-01 0.0000000E+00 1.3308000E+01 3.8540000E+00 1 0.0 0.0 0.0 +6.8333000E+00 -5.9469375E-02 -2.5141635E-01 0.0000000E+00 1.3308000E+01 4.1670000E+00 2 0.0 0.0 0.0 +1.0250000E+01 -1.0909141E-01 -4.6120149E-01 0.0000000E+00 1.3308000E+01 4.5570000E+00 3 0.0 0.0 0.0 +1.4350000E+01 -1.1573354E-01 -5.6986665E-01 0.0000000E+00 1.1480000E+01 4.6520000E+00 4 0.0 0.0 0.0 +1.8450000E+01 -9.8316709E-02 -5.4850833E-01 0.0000000E+00 1.0162000E+01 4.4580000E+00 4 0.0 0.0 0.0 +2.2550000E+01 -8.3186967E-02 -5.2457001E-01 0.0000000E+00 9.0110000E+00 4.2490000E+00 5 0.0 0.0 0.0 +2.6650000E+01 -6.7933232E-02 -4.9624675E-01 0.0000000E+00 7.7950000E+00 4.0070000E+00 6 0.0 0.0 0.0 +3.0750000E+01 -5.3393159E-02 -4.6544755E-01 0.0000000E+00 6.5440000E+00 3.7480000E+00 6 0.0 0.0 0.0 +3.4850000E+01 -4.0899260E-02 -4.3583519E-01 0.0000000E+00 5.3610000E+00 3.5020000E+00 7 0.0 0.0 0.0 +3.8950000E+01 -2.9722933E-02 -4.0591323E-01 0.0000000E+00 4.1880000E+00 3.2560000E+00 7 0.0 0.0 0.0 +4.3050000E+01 -2.0511081E-02 -3.7569051E-01 0.0000000E+00 3.1250000E+00 3.0100000E+00 8 0.0 0.0 0.0 +4.7150000E+01 -1.3980013E-02 -3.4521705E-01 0.0000000E+00 2.3190000E+00 2.7640000E+00 8 0.0 0.0 0.0 +5.1250000E+01 -8.3819737E-03 -3.1463837E-01 0.0000000E+00 1.5260000E+00 2.5180000E+00 8 0.0 0.0 0.0 +5.4666700E+01 -4.3546914E-03 -2.8909220E-01 0.0000000E+00 8.6300000E-01 2.3130000E+00 8 0.0 0.0 0.0 +5.7400000E+01 -1.6838383E-03 -2.6074456E-01 0.0000000E+00 3.7000000E-01 2.0860000E+00 8 0.0 0.0 0.0 +6.0133300E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 +6.1499900E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 + +!bjj: because of precision in the BD-AD coupling, 61.5m didn't work, so I changed it to 61.4999m +6.1500000E+01 -3.2815226E-04 -1.7737470E-01 0.0000000E+00 1.0600000E-01 1.4190000E+00 8 0.0 0.0 0.0 diff --git a/tests/unit_tests/external/CMakeLists.txt b/tests/unit_tests/external/CMakeLists.txt index 83e815b6..902d37ce 100644 --- a/tests/unit_tests/external/CMakeLists.txt +++ b/tests/unit_tests/external/CMakeLists.txt @@ -1,5 +1,6 @@ -# Specify the ROSCO controller test source files for the unit test executable -if (OpenTurbine_BUILD_ROSCO_CONTROLLER) +# Test ROSCO controller +if (OpenTurbine_BUILD_ROSCO_CONTROLLER AND + (NOT OpenTurbine_ENABLE_SANITIZER_LEAK)) target_sources( openturbine_unit_tests PRIVATE @@ -7,4 +8,12 @@ if (OpenTurbine_BUILD_ROSCO_CONTROLLER) ) endif() - +# Test AeroDyn Inflow +if (OpenTurbine_BUILD_OPENFAST_ADI AND + (NOT OpenTurbine_ENABLE_SANITIZER_LEAK)) + target_sources( + openturbine_unit_tests + PRIVATE + test_aerodyn_inflow.cpp + ) +endif() diff --git a/tests/unit_tests/external/ad_primary.dat b/tests/unit_tests/external/ad_primary.dat new file mode 100644 index 00000000..79c80a8c --- /dev/null +++ b/tests/unit_tests/external/ad_primary.dat @@ -0,0 +1,185 @@ +------- AERODYN INPUT FILE -------------------------------------------------------------------------- +NREL 5.0 MW offshore baseline aerodynamic input properties. +====== General Options ============================================================================ +False Echo - Echo the input to ".AD.ech"? (flag) +"default" DTAero - Time interval for aerodynamic calculations {or "default"} (s) +1 Wake_Mod - Wake/induction model (switch) {0=none, 1=BEMT, 3=OLAF} [Wake_Mod cannot be 2 or 3 when linearizing] +0 TwrPotent - Type tower influence on wind based on potential flow around the tower (switch) {0=none, 1=baseline potential flow, 2=potential flow with Bak correction} +0 TwrShadow - Calculate tower influence on wind based on downstream tower shadow (switch) {0=none, 1=Powles model, 2=Eames model} +False TwrAero - Calculate tower aerodynamic loads? (flag) +False CavitCheck - Perform cavitation check? (flag) [UA_Mod must be 0 when CavitCheck=true] +False Buoyancy - Include buoyancy effects? (flag) +False NacelleDrag - Include Nacelle Drag effects? (flag) +False CompAA - Flag to compute AeroAcoustics calculation [used only when Wake_Mod = 1 or 2] +"unused" AA_InputFile - AeroAcoustics input file [used only when CompAA=true] +====== Environmental Conditions =================================================================== +"default" AirDens - Air density (kg/m^3) +"default" KinVisc - Kinematic viscosity of working fluid (m^2/s) +"default" SpdSound - Speed of sound in working fluid (m/s) +"default" Patm - Atmospheric pressure (Pa) [used only when CavitCheck=True] +"default" Pvap - Vapour pressure of working fluid (Pa) [used only when CavitCheck=True] +====== Blade-Element/Momentum Theory Options ====================================================== [unused when Wake_Mod=0 or 3, except for BEM_Mod] +1 BEM_Mod - BEM model {1=legacy NoSweepPitchTwist, 2=polar} (switch) [used for all Wake_Mod to determine output coordinate system] +--- Skew correction +0 Skew_Mod - Skew model {0=No skew model, -1=Remove non-normal component for linearization, 1=skew model active} +False SkewMomCorr - Turn the skew momentum correction on or off [used only when Skew_Mod=1] +default SkewRedistr_Mod - Type of skewed-wake correction model (switch) {0=no redistribution, 1=Glauert/Pitt/Peters, default=1} [used only when Skew_Mod=1] +"default" SkewRedistrFactor - Constant used in Pitt/Peters skewed wake model {or "default" is 15/32*pi} (-) [used only when Skew_Mod=1 and SkewRedistr_Mod=1] +--- BEM algorithm +True TipLoss - Use the Prandtl tip-loss model? (flag) [unused when Wake_Mod=0 or 3] +True HubLoss - Use the Prandtl hub-loss model? (flag) [unused when Wake_Mod=0 or 3] +True TanInd - Include tangential induction in BEMT calculations? (flag) [unused when Wake_Mod=0 or 3] +False AIDrag - Include the drag term in the axial-induction calculation? (flag) [unused when Wake_Mod=0 or 3] +False TIDrag - Include the drag term in the tangential-induction calculation? (flag) [unused when Wake_Mod=0,3 or TanInd=FALSE] +"Default" IndToler - Convergence tolerance for BEMT nonlinear solve residual equation {or "default"} (-) [unused when Wake_Mod=0 or 3] +100 MaxIter - Maximum number of iteration steps (-) [unused when Wake_Mod=0] +--- Shear correction +False SectAvg - Use sector averaging (flag) +1 SectAvgWeighting - Weighting function for sector average {1=Uniform, default=1} within a sector centered on the blade (switch) [used only when SectAvg=True] +default SectAvgNPoints - Number of points per sectors (-) {default=5} [used only when SectAvg=True] +default SectAvgPsiBwd - Backward azimuth relative to blade where the sector starts (<=0) {default=-60} (deg) [used only when SectAvg=True] +default SectAvgPsiFwd - Forward azimuth relative to blade where the sector ends (>=0) {default=60} (deg) [used only when SectAvg=True] +--- Dynamic wake/inflow +0 DBEMT_Mod - Type of dynamic BEMT (DBEMT) model {0=No Dynamic Wake, -1=Frozen Wake for linearization, 1:constant tau1, 2=time-dependent tau1, 3=constant tau1 with continuous formulation} (-) +4 tau1_const - Time constant for DBEMT (s) [used only when DBEMT_Mod=1 or 3] +====== OLAF -- cOnvecting LAgrangian Filaments (Free Vortex Wake) Theory Options ================== [used only when Wake_Mod=3] +"unused" OLAFInputFileName - Input file for OLAF [used only when Wake_Mod=3] +====== Unsteady Airfoil Aerodynamics Options ==================================================== +False AoA34 - Sample the angle of attack (AoA) at the 3/4 chord or the AC point {default=True} [always used] +0 UA_Mod - Unsteady Aero Model Switch (switch) {0=Quasi-steady (no UA), 2=B-L Gonzalez, 3=B-L Minnema/Pierce, 4=B-L HGM 4-states, 5=B-L HGM+vortex 5 states, 6=Oye, 7=Boeing-Vertol} +True FLookup - Flag to indicate whether a lookup for f' will be calculated (TRUE) or whether best-fit exponential equations will be used (FALSE); if FALSE S1-S4 must be provided in airfoil input files (flag) [used only when AFAeroMod=2] +3 IntegrationMethod - Switch to indicate which integration method UA uses (1=RK4, 2=AB4, 3=ABM4, 4=BDF2) +0 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAStartRad=0] +1 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius [0.0,1.0]) [used only when UA_Mod>0; if line is missing UAEndRad=1] +====== Airfoil Information ========================================================================= +1 AFTabMod - Interpolation method for multiple airfoil tables {1=1D interpolation on AoA (first table only); 2=2D interpolation on AoA and Re; 3=2D interpolation on AoA and UserProp} (-) +1 InCol_Alfa - The column in the airfoil tables that contains the angle of attack (-) +2 InCol_Cl - The column in the airfoil tables that contains the lift coefficient (-) +3 InCol_Cd - The column in the airfoil tables that contains the drag coefficient (-) +4 InCol_Cm - The column in the airfoil tables that contains the pitching-moment coefficient; use zero if there is no Cm column (-) +0 InCol_Cpmin - The column in the airfoil tables that contains the Cpmin coefficient; use zero if there is no Cpmin column (-) +8 NumAFfiles - Number of airfoil files used (-) +"5MW_Baseline/Airfoils/Cylinder1.dat" AFNames - Airfoil file names (NumAFfiles lines) (quoted strings) +"5MW_Baseline/Airfoils/Cylinder2.dat" +"5MW_Baseline/Airfoils/DU40_A17.dat" +"5MW_Baseline/Airfoils/DU35_A17.dat" +"5MW_Baseline/Airfoils/DU30_A17.dat" +"5MW_Baseline/Airfoils/DU25_A17.dat" +"5MW_Baseline/Airfoils/DU21_A17.dat" +"5MW_Baseline/Airfoils/NACA64_A17.dat" +====== Rotor/Blade Properties ===================================================================== +True UseBlCm - Include aerodynamic pitching moment in calculations? (flag) +"5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat" ADBlFile(1) - Name of file containing distributed aerodynamic properties for Blade #1 (-) +"5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat" ADBlFile(2) - Name of file containing distributed aerodynamic properties for Blade #2 (-) [unused if NumBl < 2] +"5MW_Baseline/NRELOffshrBsline5MW_AeroDyn_blade.dat" ADBlFile(3) - Name of file containing distributed aerodynamic properties for Blade #3 (-) [unused if NumBl < 3] +====== Hub Properties ============================================================================== [used only when Buoyancy=True] +0.0 VolHub - Hub volume (m^3) +0.0 HubCenBx - Hub center of buoyancy x direction offset (m) +====== Nacelle Properties ========================================================================== [used only when Buoyancy=True or NacelleDrag=True] +0.0 VolNac - Nacelle volume (m^3) +0.0, 0.0, 0.0 NacCenB - Position of nacelle center of buoyancy from yaw bearing in nacelle coordinates (m) +0, 0, 0 NacArea - Projected area of the nacelle in X, Y, Z in the nacelle coordinate system (m^2) +0, 0, 0 NacCd - Drag coefficient for the nacelle areas defined above (-) +0, 0, 0 NacDragAC - Position of aerodynamic center of nacelle drag in nacelle coordinates (m) +====== Tail Fin Aerodynamics ======================================================================= +False TFinAero - Calculate tail fin aerodynamics model (flag) +"unused" TFinFile - Input file for tail fin aerodynamics [used only when TFinAero=True] +====== Tower Influence and Aerodynamics ============================================================ [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +11 NumTwrNds - Number of tower nodes used in the analysis (-) [used only when TwrPotent/=0, TwrShadow/=0, TwrAero=True, or Buoyancy=True] +TwrElev TwrDiam TwrCd TwrTI TwrCb ! TwrTI used only when TwrShadow=2; TwrCb used only when Buoyancy=True +(m) (m) (-) (-) (-) +1.0000000E+01 6.5000000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +1.7760000E+01 6.2400000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +2.5520000E+01 5.9700000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +3.3280000E+01 5.7100000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +4.1040000E+01 5.4500000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +4.8800000E+01 5.1800000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +5.6560000E+01 4.9200000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +6.4320000E+01 4.6600000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +7.2080000E+01 4.4000000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +7.9840000E+01 4.1300000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +8.7600000E+01 3.8700000E+00 1.0000000E+00 1.0000000E-01 0.0000000E+00 +====== Outputs ==================================================================================== +True SumPrint - Generate a summary file listing input options and interpolated properties to ".AD.sum"? (flag) +3 NBlOuts - Number of blade node outputs [0 - 9] (-) +1, 9, 19 BlOutNd - Blade nodes whose values will be output (-) +0 NTwOuts - Number of tower node outputs [0 - 9] (-) +1, 2, 6 TwOutNd - Tower nodes whose values will be output (-) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"RtAeroCp" +"RtAeroCt" +"RtAeroCq" +"RtTSR" +"RtSpeed, RtSkew, B1Azimuth" +"B1N1VDisx, B1N1VDisy, B1N1VDisz" ! disturbed wind velocity at Blade 1, Node 1 +"B1N2VDisx, B1N2VDisy, B1N2VDisz" ! disturbed wind velocity at Blade 1, Node 2 +"B1N3VDisx, B1N3VDisy, B1N3VDisz" ! disturbed wind velocity at Blade 1, Node 3 +"B1N1STVx, B1N1STVy, B1N1STVz" ! structural translational velocity at Blade 1, Node 1 +"B1N2STVx, B1N2STVy, B1N2STVz" ! structural translational velocity at Blade 1, Node 2 +"B1N3STVx, B1N3STVy, B1N3STVz" ! structural translational velocity at Blade 1, Node 2 +"B1N1AxInd, B1N2AxInd, B1N3AxInd" +"B1N1Alpha, B1N2Alpha, B1N3Alpha" +"B1N1Theta, B1N2Theta, B1N3Theta" +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) + + +#### The following was for testing, but bloats the regression test case too much +#---------------------- NODE OUTPUTS -------------------------------------------- +#3 BldNd_BladesOut - Number of blades to output all node information at. Up to number of blades on turbine. (-) +#ALL BldNd_BlOutNd - Specify a portion of the nodes to output. {"ALL", "Tip", "Root", or a list of node numbers} (-) + # OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx, AeroDyn_Nodes tab for a listing of available output channels, (-) +#"VUndx" - x-component of undisturbed wind velocity at each node +#"VUndy" - y-component of undisturbed wind velocity at each node +#"VUndz" - z-component of undisturbed wind velocity at each node +#"VDisx" - x-component of disturbed wind velocity at each node +#"VDisy" - y-component of disturbed wind velocity at each node +#"VDisz" - z-component of disturbed wind velocity at each node +#"STVx" - x-component of structural translational velocity at each node +#"STVy" - y-component of structural translational velocity at each node +#"STVz" - z-component of structural translational velocity at each node +#"VRel" - Relvative wind speed at each node +#"DynP" - Dynamic pressure at each node +#"Re" - Reynolds number (in millions) at each node +#"M" - Mach number at each node +#"Vindx" - Axial induced wind velocity at each node +#"Vindy" - Tangential induced wind velocity at each node +#"AxInd" - Axial induction factor at each node +#"TnInd" - Tangential induction factor at each node +#"Alpha" - Angle of attack at each node +#"Theta" - Pitch+Twist angle at each node +#"Phi" - Inflow angle at each node +#"Curve" - Curvature angle at each node +#"Cl" - Lift force coefficient at each node +#"Cd" - Drag force coefficient at each node +#"Cm" - Pitching moment coefficient at each node +#"Cx" - Normal force (to plane) coefficient at each node +#"Cy" - Tangential force (to plane) coefficient at each node +#"Cn" - Normal force (to chord) coefficient at each node +#"Ct" - Tangential force (to chord) coefficient at each node +#"Fl" - Lift force per unit length at each node +#"Fd" - Drag force per unit length at each node +#"Mm" - Pitching moment per unit length at each node +#"Fx" - Normal force (to plane) per unit length at each node +#"Fy" - Tangential force (to plane) per unit length at each node +#"Fn" - Normal force (to chord) per unit length at each node +#"Ft" - Tangential force (to chord) per unit length at each node +#"Clrnc" - Tower clearance at each node (based on the absolute distance to the nearest point in the tower from blade node B#N# minus the local tower radius, in the deflected configuration); please note that this clearance is only approximate because the calculation assumes that the blade is a line with no volume (however, the calculation does use the local tower radius); when blade node B#N# is above the tower top (or below the tower base), the absolute distance to the tower top (or base) minus the local tower radius, in the deflected configuration, is output +#"Vx" - Local axial velocity +#"Vy" - Local tangential velocity +#"GeomPhi" - Geometric phi? If phi was solved using normal BEMT equations, GeomPhi = 1; otherwise, if it was solved geometrically, GeomPhi = 0. +#"Chi" - Skew angle (used in skewed wake correction) -- not available for OLAF +#"UA_Flag" - Flag indicating if UA is turned on for this node. -- not available for OLAF +#"CpMin" - Pressure coefficient +#"SgCav" - Cavitation number +#"SigCr" - Critical cavitation number +#"Gam" - Gamma -- circulation on blade +#"Cl_Static" - Static portion of lift force coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +#"Cd_Static" - Static portion of drag force coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +#"Cm_Static" - Static portion of pitching moment coefficient at each node, without unsteady effects -- not available for BEMT/DBEMT +#"Uin" - Axial induced velocity in rotating hub coordinates. Axial aligned with hub axis. rotor plane polar hub rotating coordinates +#"Uit" - Tangential induced velocity in rotating hub coordinates. Tangential to the rotation plane. Perpendicular to blade aziumth. rotor plane polar hub rotating coordinates +#"Uir" - Radial induced velocity in rotating hub coordinates. Radial outwards in rotation plane. Aligned with blade azimuth. rotor plane polar hub rotating coordinates +#END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +#--------------------------------------------------------------------------------------- +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/tests/unit_tests/external/ifw_primary.dat b/tests/unit_tests/external/ifw_primary.dat new file mode 100644 index 00000000..3ab9b34d --- /dev/null +++ b/tests/unit_tests/external/ifw_primary.dat @@ -0,0 +1,71 @@ +------- InflowWind INPUT FILE ------------------------------------------------------------------------- +Steady 8 m/s winds with no shear for FAST CertTests #20 and #25 +--------------------------------------------------------------------------------------------------------------- +False Echo - Echo input data to .ech (flag) + 1 WindType - switch for wind file type (1=steady; 2=uniform; 3=binary TurbSim FF; 4=binary Bladed-style FF; 5=HAWC format; 6=User defined; 7=native Bladed FF) + 0 PropagationDir - Direction of wind propagation (meteorological rotation from aligned with X (positive rotates towards -Y) -- degrees) (not used for native Bladed format WindType=7) + 0 VFlowAng - Upflow angle (degrees) (not used for native Bladed format WindType=7) + False VelInterpCubic - Use cubic interpolation for velocity in time (false=linear, true=cubic) [Used with WindType=2,3,4,5,7] + 1 NWindVel - Number of points to output the wind velocity (0 to 9) + 0 WindVxiList - List of coordinates in the inertial X direction (m) + 0 WindVyiList - List of coordinates in the inertial Y direction (m) + 90 WindVziList - List of coordinates in the inertial Z direction (m) +================== Parameters for Steady Wind Conditions [used only for WindType = 1] ========================= + 8 HWindSpeed - Horizontal wind speed (m/s) + 90 RefHt - Reference height for horizontal wind speed (m) + 0 PLExp - Power law exponent (-) +================== Parameters for Uniform wind file [used only for WindType = 2] ============================ +"unused" Filename_Uni - Filename of time series data for uniform wind field. (-) + 90 RefHt_Uni - Reference height for horizontal wind speed (m) + 125.88 RefLength - Reference length for linear horizontal and vertical sheer (-) +================== Parameters for Binary TurbSim Full-Field files [used only for WindType = 3] ============== +"unused" FileName_BTS - Name of the Full field wind file to use (.bts) +================== Parameters for Binary Bladed-style Full-Field files [used only for WindType = 4 or WindType = 7] ========= +"unused" FileNameRoot - WindType=4: Rootname of the full-field wind file to use (.wnd, .sum); WindType=7: name of the intermediate file with wind scaling values +False TowerFile - Have tower file (.twr) (flag) ignored when WindType = 7 +================== Parameters for HAWC-format binary files [Only used with WindType = 5] ===================== +"wasp\Output\basic_5u.bin" FileName_u - name of the file containing the u-component fluctuating wind (.bin) +"wasp\Output\basic_5v.bin" FileName_v - name of the file containing the v-component fluctuating wind (.bin) +"wasp\Output\basic_5w.bin" FileName_w - name of the file containing the w-component fluctuating wind (.bin) + 64 nx - number of grids in the x direction (in the 3 files above) (-) + 32 ny - number of grids in the y direction (in the 3 files above) (-) + 32 nz - number of grids in the z direction (in the 3 files above) (-) + 16 dx - distance (in meters) between points in the x direction (m) + 3 dy - distance (in meters) between points in the y direction (m) + 3 dz - distance (in meters) between points in the z direction (m) + 90 RefHt_Hawc - reference height; the height (in meters) of the vertical center of the grid (m) + ------------- Scaling parameters for turbulence --------------------------------------------------------- + 1 ScaleMethod - Turbulence scaling method [0 = none, 1 = direct scaling, 2 = calculate scaling factor based on a desired standard deviation] + 1 SFx - Turbulence scaling factor for the x direction (-) [ScaleMethod=1] + 1 SFy - Turbulence scaling factor for the y direction (-) [ScaleMethod=1] + 1 SFz - Turbulence scaling factor for the z direction (-) [ScaleMethod=1] + 12 SigmaFx - Turbulence standard deviation to calculate scaling from in x direction (m/s) [ScaleMethod=2] + 8 SigmaFy - Turbulence standard deviation to calculate scaling from in y direction (m/s) [ScaleMethod=2] + 2 SigmaFz - Turbulence standard deviation to calculate scaling from in z direction (m/s) [ScaleMethod=2] + ------------- Mean wind profile parameters (added to HAWC-format files) --------------------------------- + 5 URef - Mean u-component wind speed at the reference height (m/s) + 2 WindProfile - Wind profile type (0=constant;1=logarithmic,2=power law) + 0 PLExp_Hawc - Power law exponent (-) (used for PL wind profile type only) + 0.03 Z0 - Surface roughness length (m) (used for LG wind profile type only) + 0 XOffset - Initial offset in +x direction (shift of wind box) +================== LIDAR Parameters =========================================================================== + 0 SensorType - Switch for lidar configuration (0 = None, 1 = Single Point Beam(s), 2 = Continuous, 3 = Pulsed) + 0 NumPulseGate - Number of lidar measurement gates (used when SensorType = 3) + 30 PulseSpacing - Distance between range gates (m) (used when SensorType = 3) + 0 NumBeam - Number of lidar measurement beams (0-5)(used when SensorType = 1) + -200 FocalDistanceX - Focal distance co-ordinates of the lidar beam in the x direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceY - Focal distance co-ordinates of the lidar beam in the y direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) + 0 FocalDistanceZ - Focal distance co-ordinates of the lidar beam in the z direction (relative to hub height) (only first coordinate used for SensorType 2 and 3) (m) +0.0 0.0 0.0 RotorApexOffsetPos - Offset of the lidar from hub height (m) + 17 URefLid - Reference average wind speed for the lidar[m/s] + 0.25 MeasurementInterval - Time between each measurement [s] + False LidRadialVel - TRUE => return radial component, FALSE => return 'x' direction estimate + 1 ConsiderHubMotion - Flag whether to consider the hub motion's impact on Lidar measurements +====================== OUTPUT ================================================== +False SumPrint - Print summary data to .IfW.sum (flag) + OutList - The next line(s) contains a list of output parameters. See OutListParameters.xlsx for a listing of available output channels, (-) +"Wind1VelX" X-direction wind velocity at point WindList(1) +"Wind1VelY" Y-direction wind velocity at point WindList(1) +"Wind1VelZ" Z-direction wind velocity at point WindList(1) +END of input file (the word "END" must appear in the first 3 columns of this last OutList line) +--------------------------------------------------------------------------------------- diff --git a/tests/unit_tests/regression/test_aerodyn_inflow.cpp b/tests/unit_tests/external/test_aerodyn_inflow.cpp similarity index 97% rename from tests/unit_tests/regression/test_aerodyn_inflow.cpp rename to tests/unit_tests/external/test_aerodyn_inflow.cpp index d4fc37b7..7a46bf01 100644 --- a/tests/unit_tests/regression/test_aerodyn_inflow.cpp +++ b/tests/unit_tests/external/test_aerodyn_inflow.cpp @@ -1,11 +1,8 @@ -#include #include -#include "test_utilities.hpp" - #include "src/utilities/aerodynamics/aerodyn_inflow.hpp" -#include "src/vendor/dylib/dylib.hpp" +#include "tests/unit_tests/regression/test_utilities.hpp" namespace openturbine::tests { @@ -505,15 +502,8 @@ TEST(AerodynInflowTest, JoinStringArray_NullCharacters) { std::string GetSharedLibraryPath() { const std::filesystem::path project_root = FindProjectRoot(); const std::filesystem::path full_path = - project_root / "build/tests/unit_tests/libaerodyn_inflow_c_binding"; - -#ifdef __APPLE__ - return full_path.string() + ".dylib"; -#elif __linux__ - return full_path.string() + ".so"; -#else // Windows - return full_path.string() + ".dll"; -#endif + project_root / "build/tests/unit_tests/aerodyn_inflow_c_binding.dll"; + return full_path.string(); } TEST(AerodynInflowTest, AeroDynInflowLibrary_DefaultConstructor) { @@ -582,9 +572,7 @@ TEST(AerodynInflowTest, AeroDynInflowLibrary_FullLoop) { // Initialize with input files const std::filesystem::path project_root = FindProjectRoot(); - std::filesystem::path input_path = project_root / - "build/external/OpenFAST_ADI/src/OpenFAST_ADI/reg_tests/" - "r-test/modules/aerodyn/py_ad_5MW_OC4Semi_WSt_WavesWN/"; + std::filesystem::path input_path = project_root / "tests/unit_tests/external/"; std::vector adiAD_input_string_array = {(input_path / "ad_primary.dat").string()}; std::vector adiIfW_input_string_array = {(input_path / "ifw_primary.dat").string()}; diff --git a/tests/unit_tests/regression/CMakeLists.txt b/tests/unit_tests/regression/CMakeLists.txt index 79355acf..fdbaac59 100644 --- a/tests/unit_tests/regression/CMakeLists.txt +++ b/tests/unit_tests/regression/CMakeLists.txt @@ -11,5 +11,4 @@ target_sources( test_utilities.cpp test_controller.cpp test_yaml_parser.cpp - test_aerodyn_inflow.cpp )