ComputeAirfoilCoeff:
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Computes lift, drag and moment coefficients.
Type ComputeAirfoilCoeff for a demo
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Form:
[cL, cD, cM] = ComputeAirfoilCoeff( g, alpha )
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Inputs
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g (1,1) Data structure
.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
alpha (1,:) Angle of attack (rad)
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Outputs
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cL (1,:) Lift coefficient
cD (1,:) Drag coefficient
cM (1,:) Moment coefficient
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Children:
Common: Graphics/Plot2D
WindTurbine: AirfoilData/LoadAirfoilFile
