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
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m (1,:) Mach number
gamma (1,1) Ratio of specific heats
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Outputs
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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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AerospaceUtils: AeroData/AtmData AerospaceUtils: AtmosphericCalculations/AtmGamma Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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