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   Mass inflow for a supersonic diffuser
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   Form:
   mA = MassInflowSupersonic( gamma, machNo2, piD, p0, t0, tauR )
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   Inputs
   ------
   gamma      (1,1)   Ratio of specific heats
   machNo2    (1,1)   Mach number at station 2
   piD        (1,1)   Diffuser pressure ratio (nearly 1)
   altitude   (1,1)   Altitude (m)
   cP         (1,1)   Specific heat constant pressure
   machNo     (1,:)   Mach number
   units      (1,:)   'eng' or 'mks'

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   Outputs
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   mA         (1,:)   mdot/a

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