InducedDragCoeff:

Path: ACPro/ACProAerodynamics

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   Induced drag coefficient for all Mach numbers.

   At supersonic speeds provides combined vortex and wave drag. 
   Drag is cD0 + k*cL^2.

   This function includes a linear term in the square root for the
   supersonic mach numbers that allows it to match the
   subsonic induced drag at M = 1. Otherwise it would produce a jump in
   the drag at M = 1.

   Type InducedDragCoeff for a demo

   Since version 4 (ACT).
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   Form:
   k = InducedDragCoeff( e, aR, m )
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   ------
   Inputs
   ------
   e              (1,1) Oswald efficiency factor (0 to 1)
   aR             (1,1) Wing aspect ratio
   m              (1,:) Mach number

   -------
   Outputs
   -------
   k              (1,:) Induced drag coefficient

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   Reference: http://adg.stanford.edu/aa241/drag/LiftWaveDrag.html
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Children:

Common: Graphics/Plot2D

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