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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
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gamma (1,:) Ratio of specific heats
m (1,:) Mach number
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Outputs
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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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AC: Aero/RayleighPitotTube Common: Graphics/Plot2D
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