StaticStall:
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Static Stall Model
This model simply returns the lift, drag and moment coefficients by
looking up the airfoil data files. The static stall information is
contained in the raw airfoil data
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Form:
[CL,CD,CM] = StaticStall(af,bld,Reb,thknss,alpha,alphadot,c,W)
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Inputs
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af (1,1) Airfoil data structure
.reCL (1,:) Reynolds number
.alphaCL (1,:) Angle of attack (deg)
.cL (:,:) Lift coefficient
.reCD (1,:) Drag Reynolds number
.alphaCD (1,:) Angle of attack (deg)
.cD (:,:) Drag coefficient
.reCM (1,:) Reynolds number
.alphaCM (1,:) Angle of attack (deg)
.cM (:,:) Moment coefficient
.alpha0 (1,1) Angle of atack for zero lift
bld (1,1) Blade data structure [NOT USED]
.c (1,1) Chord (m)
.H (1,1) Blade half length (m)
.thknss (1,1) Blade thickness (m)
Reb (1,1) Blade Reynolds number
alpha (1,1) Angle of attack (rad)
alphadot (1,1) Angle of attack rate (rad/s) [NOT USED]
W (1,1) Relative wind speed (m/s)
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Outputs
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CL (1,1) Blade lift coefficient
CD (1,1) Blade drag coefficient
CM (1,1) Blade moment coefficient
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