ConcordeLD:

Path: ACPro/ACProAerodynamics

% Optimal lift and drag coefficients for the Concorde.
 Output is  function of Mach number.
 Type ConcordeLD for a demo

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   Form:
   [cL, cD, k1, k2] = ConcordeLD( m )
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   ------
   Inputs
   ------
   m          (1,:) Mach number

   -------
   Outputs
   -------
   cL         (1,:) Lift coefficient
   cD         (1,:) Drag coefficient
   k1         (1,:) Drag at zero lift
   k2         (1,:) Drag from lift coefficient (Induced drag)

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   Reference: Austyn Mair, W. and D.L.L. Birdsall (1992.) 
              Aircraft Performance. Cambridge. pp. 40-41 and p.261.
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Children:

Common: Graphics/Plot2D

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