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OpenFAST
Wind turbine multiphysics simulator
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OpenFAST
Wind turbine multiphysics simulator
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Public Attributes | |
| real(reki) | alpha0 |
| Angle of attack for zero lift (also used in HGM) [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) | c_lalpha |
| Cl slope for zero lift (used for HGM unsteady aero only) -> calculated [1/rad]. | |
| real(reki) | t_f0 |
| initial value of T_f, airfoil specific, used to compute D_f and fprimeprime (also used in HGM) [-] | |
| 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 (also used in HGM) [-] | |
| 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 (also used in HGM), usually 0.14 [-] | |
| real(reki) | b2 |
| airfoil constant derived from experimental results (also used in HGM), usually 0.53 [-] | |
| real(reki) | b5 |
| airfoil constant derived from experimental results, usually 5.0 [-] | |
| real(reki) | a1 |
| airfoil constant derived from experimental results (also used in HGM), usually 0.3 [-] | |
| real(reki) | a2 |
| airfoil constant derived from experimental results (also used in HGM), 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 [or critical value of Cn_prime at LE separation for alpha >= alpha0] [-]. | |
| real(reki) | cn2 |
| Cn at stall value for negative angle of attack [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 [-]. | |
| 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) | uacutout_delta |
| Number of angles-of-attack below UACutout where unsteady aerodynamics begin to be disabled [input in degrees; stored as radians]. | |
| real(reki) | uacutout_blend |
| Angle of attack above which unsteady aerodynamics begins to be disabled [stored as radians]. | |
| real(reki) | filtcutoff |
| Reduced frequency cutoff used to calculate the dynamic low pass filter cut-off frequency for the pitching rate and accelerations [default = 0.5] [-]. | |
| real(reki) | alphaupper |
| (input) upper angle of attack defining fully attached region [input in degrees; stored as radians] | |
| real(reki) | alphalower |
| (input) lower angle of attack defining fully attached region [input in degrees; stored as radians] | |
| real(reki) | c_rate |
| (calculated) linear slope in the fully attached region of cn or cl [1/rad] | |
| real(reki) | c_rateupper |
| (calculated) linear slope in the upper fully attached region of cn or cl [1/rad] | |
| real(reki) | c_ratelower |
| (calculated) linear slope in the lower fully attached region of cn or cl [1/rad] | |
| real(reki) | c_alphalower |
| (calculated) value of cn or cl at alphaLower [-] | |
| real(reki) | c_alphaupper |
| (calculated) value of cn or cl at alphaUpper [-] | |
| real(reki) | alphaupperwrap |
| (calculated) upper angle of attack defining fully attached wrap-around region [stored as radians] | |
| real(reki) | alphalowerwrap |
| (calculated) lower angle of attack defining fully attached wrap-around region [stored as radians] | |
| real(reki) | c_ratewrap |
| (calculated) linear slope in the fully attached wrap-around region of cn or cl (will be negative) [1/rad] | |
| real(reki) | c_alphalowerwrap |
| (calculated) value of cn or cl at alphaLowerWrap [-] | |
| real(reki) | c_alphaupperwrap |
| (calculated) value of cn or cl at alphaUpperWrap [-] | |
| 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] [-]
1.8.13