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New features for unsteady aerodynamics modeling #729

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Sep 20, 2021
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New features for unsteady aerodynamics modeling #729

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a8ff0b2
merge NREL/dev into bjonkman/UA
bjonkman Jun 28, 2021
8bf7a77
AD/UA: fix sign on `vx_34` per email from ebranlard
bjonkman Jun 28, 2021
220ae9a
Minor fix to api_change.rst (UAStart/End in wrong table)
andrew-platt Aug 6, 2021
2368a12
Merge remote-tracking branch 'NREL/dev' into f/UA
bjonkman Sep 15, 2021
b861587
minor fix for builds with different precision
bjonkman Sep 15, 2021
b682cbe
update r-test pointer
bjonkman Sep 15, 2021
bab6da5
remove comment
bjonkman Sep 15, 2021
c5d76d5
add comment from 'f/LinearAero' branch
bjonkman Sep 15, 2021
1b189c4
docs: fix typo
bjonkman Sep 15, 2021
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69 changes: 36 additions & 33 deletions docs/source/user/aerodyn/examples/ad_airfoil_example.inp
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Expand Up @@ -86,40 +86,43 @@
! ------------------------------------------------------------------------------
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
true InclUAdata ! Is unsteady aerodynamics data included in this table? If TRUE, then include UA coefficients below this line
!........................................
-0.38 alpha0 ! 0-lift angle of attack, depends on airfoil.
15.3 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg)
-15.3 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA<alpha0. (deg)
1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-)
7.12499 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad)
2 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3]
7 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. It depends on…
1.6 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. It should be tuned based on airfoil experimental…
9 T_VL ! Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-…
"Default" b1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different…
"Default" b2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different…
0.5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5]
"Default" A1 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different…
"Default" A2 ! Constant in the expression of phi_alpha^c and phi_q^c. This value is relatively insensitive for thin airfoils, but may be different…
"Default" A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1]
18.269 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
-11.324 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1]
18.269 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1]
-11.324 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1]
1.9408 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. It…
-0.8 Cn2 ! As Cn1 for negative AOAs.
"Default" St_sh ! Strouhal's shedding frequency constant. [default = 0.19]
0.0016 Cd0 ! 2D drag coefficient value at 0-lift.
-0.0328 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. [If the aerodynamics coefficients table does…
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]
-0.38 alpha0 ! 0-lift angle of attack, depends on airfoil. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
15.3 alpha1 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA>alpha0. (deg) ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-15.3 alpha2 ! Angle of attack at f=0.7, (approximately the stall angle) for AOA<alpha0. (deg) ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
5 alphaUpper ! Angle of attack at upper boundary of fully-attached region. (deg) [used only when UAMod=5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-3 alphaLower ! Angle of attack at lower boundary of fully-attached region. (deg) [used only when UAMod=5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
1 eta_e ! Recovery factor in the range [0.85 - 0.95] used only for UAMOD=1, it is set to 1 in the code when flookup=True. (-) ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 1
7.12499 C_nalpha ! Slope of the 2D normal force coefficient curve. (1/rad) ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
2 T_f0 ! Initial value of the time constant associated with Df in the expression of Df and f''. [default = 3] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
7 T_V0 ! Initial value of the time constant associated with the vortex lift decay process; it is used in the expression of Cvn. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
1.6 T_p ! Boundary-layer,leading edge pressure gradient time constant in the expression of Dp. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
9 T_VL ! Initial value of the time constant associated with the vortex advection process; ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"Default" b1 ! Constant in the expression of phi_alpha^c and phi_q^c. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"Default" b2 ! Constant in the expression of phi_alpha^c and phi_q^c. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.5 b5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 5; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"Default" A1 ! Constant in the expression of phi_alpha^c and phi_q^c. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"Default" A2 ! Constant in the expression of phi_alpha^c and phi_q^c. ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"Default" A5 ! Constant in the expression of K'''_q,Cm_q^nc, and k_m,q. [from experimental results, defaults to 1; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
18.269 S1 ! Constant in the f curve best-fit for alpha0<=AOA<=alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
-11.324 S2 ! Constant in the f curve best-fit for AOA> alpha1; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
18.269 S3 ! Constant in the f curve best-fit for alpha2<=AOA< alpha0; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
-11.324 S4 ! Constant in the f curve best-fit for AOA< alpha2; by definition it depends on the airfoil. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
1.9408 Cn1 ! Critical value of C0n at leading edge separation. It should be extracted from airfoil data at a given Mach and Reynolds number. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-0.8 Cn2 ! As Cn1 for negative AOAs. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
"Default" St_sh ! Strouhal's shedding frequency constant. [default = 0.19; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
0.0016 Cd0 ! 2D drag coefficient value at 0-lift. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
-0.0328 Cm0 ! 2D pitching moment coefficient about 1/4-chord location, at 0-lift, positive if nose up. ! THIS IS AN OPTIONAL LINE; if omitted, it will be calculated from the polar data
0 k0 ! Constant in the \hat(x)_cp curve best-fit; = (\hat(x)_AC-0.25). [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 k1 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 k2 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 k3 ! Constant in the \hat(x)_cp curve best-fit. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
0 k1_hat ! Constant in the expression of Cc due to leading edge vortex effects. [ignored if UAMod<>1] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to 0
"Default" x_cp_bar ! Constant in the expression of \hat(x)_cp^v. [ignored if UAMod<>1, default = 0.2] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"DEFAULT" UACutout ! Angle of attack above which unsteady aerodynamics are disabled (deg). [Specifying the string "Default" sets UACutout to 45 degrees] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"DEFAULT" UACutout_delta ! Delta angle of attack below UACutout where unsteady aerodynamics begin to turn off (blend with steady solution) (deg) [Specifying the string "Default" sets UACutout_delta to 5 degrees] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
"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; unused when UAMod = 4 or 5] ! THIS IS AN OPTIONAL LINE; if omitted, it will be set to its default value
!........................................
! Table of aerodynamics coefficients
63 NumAlf ! Number of data lines in the following table
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2 changes: 2 additions & 0 deletions docs/source/user/aerodyn/examples/ad_primary_example.inp
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Expand Up @@ -37,6 +37,8 @@ True TIDrag - Include the drag term in the tangential-induc
====== Beddoes-Leishman Unsteady Airfoil Aerodynamics Options ===================================== [used only when AFAeroMod=2]
1 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]
FALSE 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]
0.25 UAStartRad - Starting radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2; if line is missing UAStartRad=0]
0.95 UAEndRad - Ending radius for dynamic stall (fraction of rotor radius) [used only when AFAeroMod=2; 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 (-)
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