diff --git a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_AeroDyn15.dat b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_AeroDyn15.dat index f5d30014..59f6e268 100644 --- a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_AeroDyn15.dat +++ b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_AeroDyn15.dat @@ -37,6 +37,8 @@ default IndToler - Convergence tolerance for BEMT nonlinear so ====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] 3 UAMod - Unsteady Aero Model Switch (switch) {1=Baseline model (Original), 2=Gonzalez's variant (changes in Cn,Cc,Cm), 3=Minnema/Pierce variant (changes in Cc and Cm)} [used only when AFAeroMod=2] 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] +0.1 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] +1.0 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] ====== 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 (-) diff --git a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ElastoDyn_tower.dat b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ElastoDyn_tower.dat index ce2a8f04..547fa669 100644 --- a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ElastoDyn_tower.dat +++ b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ElastoDyn_tower.dat @@ -2,10 +2,10 @@ IEA 15 MW offshore reference model monopile configuration ---------------------- TOWER PARAMETERS ---------------------------------------- 20 NTwInpSt - Number of input stations to specify tower geometry -0.32 TwrFADmp(1) - Tower 1st fore-aft mode structural damping ratio (%) -0.32 TwrFADmp(2) - Tower 2nd fore-aft mode structural damping ratio (%) -0.32 TwrSSDmp(1) - Tower 1st side-to-side mode structural damping ratio (%) -0.32 TwrSSDmp(2) - Tower 2nd side-to-side mode structural damping ratio (%) +1.0 TwrFADmp(1) - Tower 1st fore-aft mode structural damping ratio (%) +1.0 TwrFADmp(2) - Tower 2nd fore-aft mode structural damping ratio (%) +1.0 TwrSSDmp(1) - Tower 1st side-to-side mode structural damping ratio (%) +1.0 TwrSSDmp(2) - Tower 2nd side-to-side mode structural damping ratio (%) ---------------------- TOWER ADJUSTMUNT FACTORS -------------------------------- 1.0 FAStTunr(1) - Tower fore-aft modal stiffness tuner, 1st mode (-) 1.0 FAStTunr(2) - Tower fore-aft modal stiffness tuner, 2nd mode (-) diff --git a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ServoDyn.dat b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ServoDyn.dat index 02934a6b..b25ce5a2 100644 --- a/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ServoDyn.dat +++ b/OpenFAST/IEA-15-240-RWT-Monopile/IEA-15-240-RWT-Monopile_ServoDyn.dat @@ -25,10 +25,10 @@ True GenTiStp - Method to stop the generator {T: timed usin 0.0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True] 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True] ---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL -------------------- -9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] -9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] -9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] -9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] +7.559987120819503 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] +19624046.66639 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] +343357.4355671095 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] +2. VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] ---------------------- SIMPLE INDUCTION GENERATOR ------------------------------ 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1] 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1] diff --git a/OpenFAST/IEA-15-240-RWT-Monopile_wDTUcontroller/IEA-15-240-RWT-Monopile_ServoDyn_wDTUcontroller.dat b/OpenFAST/IEA-15-240-RWT-Monopile_wDTUcontroller/IEA-15-240-RWT-Monopile_ServoDyn_wDTUcontroller.dat index 7c17d867..1c4c8c48 100644 --- a/OpenFAST/IEA-15-240-RWT-Monopile_wDTUcontroller/IEA-15-240-RWT-Monopile_ServoDyn_wDTUcontroller.dat +++ b/OpenFAST/IEA-15-240-RWT-Monopile_wDTUcontroller/IEA-15-240-RWT-Monopile_ServoDyn_wDTUcontroller.dat @@ -25,10 +25,10 @@ True GenTiStp - Method to stop the generator {T: timed usin 0.0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True] 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True] ---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL -------------------- -9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] -9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] -9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] -9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] +7.559987120819503 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] +19624046.66639 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] +343357.4355671095 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] +2. VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] ---------------------- SIMPLE INDUCTION GENERATOR ------------------------------ 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1] 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1] diff --git a/OpenFAST/IEA-15-240-RWT-OLAF/IEA-15-240-RWT_AeroDyn15.dat b/OpenFAST/IEA-15-240-RWT-OLAF/IEA-15-240-RWT_AeroDyn15.dat index fbcbc13c..079ada18 100644 --- a/OpenFAST/IEA-15-240-RWT-OLAF/IEA-15-240-RWT_AeroDyn15.dat +++ b/OpenFAST/IEA-15-240-RWT-OLAF/IEA-15-240-RWT_AeroDyn15.dat @@ -37,6 +37,8 @@ default IndToler - Convergence tolerance for BEMT nonlinear so ====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] 3 UAMod - Unsteady Aero Model Switch (switch) {1=Baseline model (Original), 2=Gonzalez's variant (changes in Cn,Cc,Cm), 3=Minnema/Pierce variant (changes in Cc and Cm)} [used only when AFAeroMod=2] 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] +0.1 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] +1.0 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] ====== 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 (-) diff --git a/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_AeroDyn15.dat b/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_AeroDyn15.dat index 1b14428d..81336ad4 100644 --- a/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_AeroDyn15.dat +++ b/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_AeroDyn15.dat @@ -37,6 +37,8 @@ default IndToler - Convergence tolerance for BEMT nonlinear so ====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2] 3 UAMod - Unsteady Aero Model Switch (switch) {1=Baseline model (Original), 2=Gonzalez's variant (changes in Cn,Cc,Cm), 3=Minnema/Pierce variant (changes in Cc and Cm)} [used only when AFAeroMod=2] 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] +0.1 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] +1.0 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2] ====== 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 (-) diff --git a/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat b/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat index f2d313e7..33648fe8 100644 --- a/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat +++ b/OpenFAST/IEA-15-240-RWT-UMaineSemi/IEA-15-240-RWT-UMaineSemi_ServoDyn.dat @@ -25,10 +25,10 @@ True GenTiStp - Method to stop the generator {T: timed usin 0.0 TimGenOn - Time to turn on the generator for a startup (s) [used only when GenTiStr=True] 9999.9 TimGenOf - Time to turn off the generator (s) [used only when GenTiStp=True] ---------------------- SIMPLE VARIABLE-SPEED TORQUE CONTROL -------------------- -9999.9 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] -9999.9 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] -9999.9 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] -9999.9 VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] +7.559987120819503 VS_RtGnSp - Rated generator speed for simple variable-speed generator control (HSS side) (rpm) [used only when VSContrl=1] +19624046.66639 VS_RtTq - Rated generator torque/constant generator torque in Region 3 for simple variable-speed generator control (HSS side) (N-m) [used only when VSContrl=1] +343357.4355671095 VS_Rgn2K - Generator torque constant in Region 2 for simple variable-speed generator control (HSS side) (N-m/rpm^2) [used only when VSContrl=1] +2. VS_SlPc - Rated generator slip percentage in Region 2 1/2 for simple variable-speed generator control (%) [used only when VSContrl=1] ---------------------- SIMPLE INDUCTION GENERATOR ------------------------------ 9999.9 SIG_SlPc - Rated generator slip percentage (%) [used only when VSContrl=0 and GenModel=1] 9999.9 SIG_SySp - Synchronous (zero-torque) generator speed (rpm) [used only when VSContrl=0 and GenModel=1] diff --git a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat index 34677176..4cd74ebb 100644 --- a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat +++ b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_00.dat @@ -13,41 +13,7 @@ AF00_BL.txt BL_file ! The file name including the boundary laye ! ------------------------------------------------------------------------------ 3.000000 Re ! Reynolds number in millions 0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. -0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 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. -0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] -0.000000 Cd0 ! 2D drag coefficient value at 0-lift. -0.000000 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] -0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients 200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm diff --git a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat index d3a5b8ac..955790ec 100644 --- a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat +++ b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_01.dat @@ -13,41 +13,7 @@ AF01_BL.txt BL_file ! The file name including the boundary laye ! ------------------------------------------------------------------------------ 3.000000 Re ! Reynolds number in millions 0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. -0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 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. -0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] -0.000000 Cd0 ! 2D drag coefficient value at 0-lift. -0.000000 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] -0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients 200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm diff --git a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat index 55b0fd6a..56f85273 100644 --- a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat +++ b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_02.dat @@ -13,41 +13,7 @@ AF02_BL.txt BL_file ! The file name including the boundary laye ! ------------------------------------------------------------------------------ 3.000000 Re ! Reynolds number in millions 0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ --3.932905 alpha0 ! 0-lift angle of attack, depends on airfoil. -19.926944 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) --20.460148 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.295202 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. --0.437208 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] -0.333782 Cd0 ! 2D drag coefficient value at 0-lift. --0.008236 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] -0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients 200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm diff --git a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat index a9ec7501..b05bd98b 100644 --- a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat +++ b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_03.dat @@ -13,41 +13,7 @@ AF03_BL.txt BL_file ! The file name including the boundary laye ! ------------------------------------------------------------------------------ 3.000000 Re ! Reynolds number in millions 0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. -0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 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. -0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] -0.000000 Cd0 ! 2D drag coefficient value at 0-lift. -0.000000 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] -0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients 200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm diff --git a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat index 84fc351b..2ff06c6d 100644 --- a/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat +++ b/OpenFAST/IEA-15-240-RWT/Airfoils/IEA-15-240-RWT_AeroDyn15_Polar_04.dat @@ -13,41 +13,7 @@ AF04_BL.txt BL_file ! The file name including the boundary laye ! ------------------------------------------------------------------------------ 3.000000 Re ! Reynolds number in millions 0 Ctrl ! Control setting (must be 0 for current AirfoilInfo) -True InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line -!........................................ -0.000000 alpha0 ! 0-lift angle of attack, depends on airfoil. -0.000000 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) -0.000000 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA1] -0.000000 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] -0.000000 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. -0.000000 Cn2 ! As Cn1 for negative AOAs. -Default St_sh ! Strouhal's shedding frequency constant. [default = 0.19] -0.000000 Cd0 ! 2D drag coefficient value at 0-lift. -0.000000 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] -0.000000 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] -0.000000 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] -0.000000 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] -Default x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] -Default UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] -Default filtCutOff ! Cut-off frequency (-3 dB corner frequency) for low-pass filtering the AoA input to UA, as well as the 1st and 2nd derivatives (Hz) [default = 20] -!........................................ +False InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include 30 UA coefficients below this line ! Table of aerodynamics coefficients 200 NumAlf ! Number of data lines in the following table ! Alpha Cl Cd Cm