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OpenFAST
Wind turbine multiphysics simulator
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Public Attributes | |
real(reki) | alpha0 |
Angle of attack for zero lift (used for Beddoes-Leishman unsteady aero) [input in degrees; stored as radians]. | |
real(reki) | alpha1 |
angle of attack at f = 0.7, approximately the stall angle; for alpha >= alpha0 [input in degrees; stored as radians] | |
real(reki) | alpha2 |
angle of attack at f = 0.7, approximately the stall angle; for alpha < alpha0 [input in degrees; stored as radians] | |
real(reki) | eta_e |
Recovery factor in the range [0.85 - 0.95] [-]. | |
real(reki) | c_nalpha |
Cn slope for zero lift (used for Beddoes-Leishman unsteady aero) [1/rad]. | |
real(reki) | t_f0 |
initial value of T_f, airfoil specific, used to compute D_f and fprimeprime [-] | |
real(reki) | t_v0 |
initial value of T_V, airfoil specific, time parameter associated with the vortex lift decay process, used in Cn_v [-] | |
real(reki) | t_p |
boundary-layer, leading edge pressure gradient time parameter; used in D_p; airfoil specific [-] | |
real(reki) | t_vl |
Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn. More... | |
real(reki) | b1 |
airfoil constant derived from experimental results, usually 0.14 [-] | |
real(reki) | b2 |
airfoil constant derived from experimental results, usually 0.53 [-] | |
real(reki) | b5 |
airfoil constant derived from experimental results, usually 5.0 [-] | |
real(reki) | a1 |
airfoil constant derived from experimental results, usually 0.3 [-] | |
real(reki) | a2 |
airfoil constant derived from experimental results, usually 0.7 [-] | |
real(reki) | a5 |
airfoil constant derived from experimental results, usually 1.0 [-] | |
real(reki) | s1 |
Constant in the f curve best-fit for alpha0<=AOA<=alpha1 [-]. | |
real(reki) | s2 |
Constant in the f curve best-fit for AOA> alpha1 [-]. | |
real(reki) | s3 |
Constant in the f curve best-fit for alpha2<=AOA< alpha0 [-]. | |
real(reki) | s4 |
Constant in the f curve best-fit for AOA< alpha2 [-]. | |
real(reki) | cn1 |
Cn at stall value for positive angle of attack (used for Beddoes-Leishman unsteady aero) [or critical value of Cn_prime at LE separation for alpha >= alpha0] [-]. | |
real(reki) | cn2 |
Cn at stall value for negative angle (used for Beddoes-Leishman unsteady aero) or [critical value of Cn_prime at LE separation for alpha < alpha0] [-]. | |
real(reki) | st_sh |
Strouhal's shedding frequency constant. More... | |
real(reki) | cd0 |
Minimum Cd value (used for Beddoes-Leishman unsteady aero) [-]. | |
real(reki) | cm0 |
2D pitching moment coefficient at zero lift, positive if nose is up [-] | |
real(reki) | k0 |
airfoil parameter in the x_cp_hat curve best-fit [ignored if UAMod<>1] [-] | |
real(reki) | k1 |
airfoil parameter in the x_cp_hat curve best-fit [ignored if UAMod<>1] [-] | |
real(reki) | k2 |
airfoil parameter in the x_cp_hat curve best-fit [ignored if UAMod<>1] [-] | |
real(reki) | k3 |
airfoil parameter in the x_cp_hat curve best-fit [ignored if UAMod<>1] [-] | |
real(reki) | k1_hat |
Constant in the expression of Cc due to leading edge vortex effects. More... | |
real(reki) | x_cp_bar |
Constant in the expression of (x)_cp^v [ignored if UAMod<>1, default = 0.2] [-]. | |
real(reki) | uacutout |
Angle of attack above which unsteady aerodynamics are disabled [input in degrees; stored as radians]. | |
real(reki) | filtcutoff |
low pass filter cut-off frequency for the pitching rate and accelerations [Hz] | |
real(reki) airfoilinfo_types::afi_ua_bl_type::k1_hat |
Constant in the expression of Cc due to leading edge vortex effects.
[ignored if UAMod<>1] [-]
real(reki) airfoilinfo_types::afi_ua_bl_type::st_sh |
Strouhal's shedding frequency constant.
[-]
real(reki) airfoilinfo_types::afi_ua_bl_type::t_vl |
Initial value of the time constant associated with the vortex advection process; it represents the non-dimensional time in semi-chords, needed for a vortex to travel from LE to trailing edge (TE); it is used in the expression of Cvn.
It depends on Re, M (weakly), and airfoil. [valid range = 6 - 13] [-]