CLCMWing:

Path: ACPro/ACProAerodynamics

% Lift and moment coefficients of a thin wing.
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   Form: 
              CLCMWing( alpha, z )
   [cL, cM] = CLCMWing( alpha, z )
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   ------
   Inputs
   ------
   alpha       (1,:) Angle of attack (rad)
   z           (1,:) Camber ratio z = 1/8R where R is the radius of
                     curvature

   ------
   Inputs
   ------
   cL          (1,:) Lift coefficent
   cM          (1,:) Quarter chord moment coefficient
   cL0         (1,:) Lift coefficent at zero angle of attack

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   Reference: McCormick, B. W., "Aerodynamics, Aeronautics and Flight
              Mechanics," Wiley, 1979, p. 86.
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