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
   ------
   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)

   -------
   Outputs
   -------
   cL                 (1,:) Lift coefficient
   cD                 (1,:) Drag coefficient
   cM                 (1,:) Moment coefficient

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Children:

Common: Graphics/Plot2D
WindTurbine: AirfoilData/LoadAirfoilFile