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   Optimal lift and drag coefficients for the Concorde as a function of mach
   number.
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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,:) k1
   k2         (1,:) k2

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