LiftCoeff:

Path: ACPro/ACProAerodynamics

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   Computes the ideal lift coefficient from 0 through supersonic.

   The zero mach lift coefficient is
      cL = cL0 + cLAlpha*alpha;
   Also applies the Prandtl Glauert compressibility correction. Does not
   account for stall.
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   Form:
   cL = LiftCoeff( alpha, cLAlpha, cL0, m, delta )
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   ------
   Inputs
   ------
   alpha           (1,:)  Angle of attack
   cLAlpha         (1,1)  Coefficient dcL/dAlpha
   cL0             (1,1)  Lift at zero angle of attack
   m               (1,:)  Mach number
   delta           (1,1)  If entered use the transonic damping

   -------
   Outputs
   -------
   cL              (1,:) Lift coefficient

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   See also PrandtlGlauertCorrection
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Children:

ACPro: ACProAerodynamics/PrandtlGlauertCorrection
Common: Graphics/Plot2D

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