CLComposite:

Path: ACPro/ACProAerodynamics

% Lift coefficient for subsonic, supersonic and hypersonic flight.
   
   This combines subsonic, supersonic and hypersonic. All regimes have a
   Mach number correction. If alpha is not entered it will compute just
   the lift curve coefficient.

   Type CLComposite for a demo.

   Since version 2014.1. 
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   Form:
   cL = CLComposite( m, d, alpha, gamma )
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   ------
   Inputs
   ------
   m       (1,:)	  Freestream Mach number
   d        (.)    Data structure
                   .cLM1           (1,1) Lift ratio at Mach 1
                   .cLAlpha        (1,1) Lift curve slope (1/rad)
                   .sweep          (1,1) Sweep angle (rad)
                   .thicknessRatio	(1,1) Thickness to chord ratio
   alpha   (1,:)   Angle of attack (rad)
   gamma   (1,1)   Ratio of specific heats (Default = 1.4)

   -------
   Outputs
   -------
   cL      (1,:) 	Lift coefficient
  
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   See also CPHypersonic
--------------------------------------------------------------------------

Children:

ACPro: ACProAerodynamics/CPHypersonic
Common: Graphics/Plot2D

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