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   Returns Concorde properties. The SFC and F/delta are only valid between
   M = 1 and M = 2.
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   Form:
   d = ConcordeProperties( machNo )
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   ------
   Inputs
   ------
   None

   -------
   Outputs
   -------
   d              (1,1)  Aircraft parameters
                         .massDry     (1,1)
                         .massFuel    (1,1)
                         .massDesign  (1,1) Design point for calculations
                         .sFC         (1,:) Specific fuel consumption
                         .cL          (1,:) Lift coefficient
                         .cD          (1,:) Drag coefficient
                         .k1          (1,:) Drag polar coefficient 1
                         .k2          (1,:) Drag polar coefficient 2
                         .wingArea    (1,1) Wing area (m^2)
                         .wingLoading (1,1) Wing loading
                         .name        (1,:) Name
                         .cLCoeff     (1,1) Lift coefficient
                         .cLMax       (1,1) Maximum lift coefficient
                         .fOverDelta  (1,:) Force over P/P0
   def             {:,3} Property definitions

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