CLAlpha:
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Computes the lift curve slope for an airfoil.
cL = cLAlpha*alpha with alpha in radians.
Type CLAlpha for a demo with a NACA 0012 airfoil.
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Form:
cLAlpha = CLAlpha( airfoil, rE )
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Inputs
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airfoil (1,1) Airfoil data structure
.reCL (1,:) Reynold's number
.alphaCL (1,:) Angle of attack (deg)
.cL (:,:) Lift coefficient
.reCD (1,:) Reynold's number
.alphaCD (1,:) Angle of attack (deg)
.cD (:,:) Drag coefficient
.reCM (1,:) Reynold's number
.alphaCM (1,:) Angle of attack (deg)
.cM (:,:) Moment coefficient
rE (1,1) Reynold's number
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Outputs
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cLAlpha (1,1) Lift curve slope
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Children:
Common: Graphics/Plot2D
Math: Linear/LeastSq
WindTurbine: AirfoilData/LoadAirfoilFile
