PressureRatioFromMach:

Path: AC/Aero

% Computes impact to static pressure ratio from Mach number and gamma.
   For supersonic flow uses the Rayleigh pitot tube formula.
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   Form:
   pR = PressureRatioFromMach( gamma, m )
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   ------
   Inputs
   ------
   gamma          (1,:)       Ratio of specific heats
   m              (1,:)       Mach number

   -------
   Outputs
   -------
   pR             (1,:)       Pressure ratio

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   See also: RayleighPitotTube
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   Reference: Anderson, John D. Introduction to Flight, Third Edition,
              McGraw-Hill, 1989. Ch. 4, Basic Aerodynamics
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Children:

AC: Aero/RayleighPitotTube
Common: Graphics/Plot2D

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