RayleighPitotTube:

Path: AC/Aero

% Stagnation pressure ratio in supersonic flow.
   Only valid for hypersonic flight, i.e.
         m > sqrt((gamma-1)/2*gamma)
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   Form:
   pR = RayleighPitotTube( m, gamma )
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   ------
   Inputs
   ------
   m              (1,:)  Mach number
   gamma          (1,1)  Ratio of specific heats

   -------
   Outputs
   -------
   pR             (1,:)  Pressure ratio stagnation/p at infinity

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   Reference: Anderson, John D. Introduction to Flight, Third Edition,
              McGraw-Hill, 1989. Eq. 4.79
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Children:

AerospaceUtils: AtmosphericCalculations/AtmGamma
Common: Graphics/Plot2D

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