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Path: ACPro/ACEngine
% Computes the total pressure and temperature at a Mach number.
Computes the total pressure and temperature given a pressure and
temperature of a gas flow at Mach number m.
Type TotalPressureAndTemperature for a demo at 10 km altitude.
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Form:
[p0, t0] = TotalPressureAndTemperature( p, t, gamma, m )
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Inputs
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p (1,1) Pressure
t (1,1) Temperature
gamma (1,1) Ratio of specific heats
m (1,:) Mach number
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Outputs
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p0 (1,:) Total pressure
t0 (1,:) Total temperature
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Reference: Benson, T. J., "An Interactive Educational Tool for
Turbojet Engines," May 1995, NASA Lewis Research Center
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AerospaceUtils: AtmosphericCalculations/AtmGamma Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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