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
   ------
   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

   -------
   Outputs
   -------
   cLAlpha            (1,1) Lift curve slope

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Children:

Common: Graphics/Plot2D
Math: Linear/LeastSq
WindTurbine: AirfoilData/LoadAirfoilFile