Path: ACPro/ACThermal
% Stagnation conditions for a gas.
Computes the ratio between stagnation M = 0 and the input Mach number.
Type StagnationPAndT for a demo.
Demos gives the results for air, gamma = 1.4 from Mach 0 to 6.
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Form:
[pR, tR] = Stagnation( 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
tR (1,:) Temperature ratio
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Reference: P. G. Hill, C. R. Peterson, "The Mechanics and
Thermodynamics of Propulsion," Addison-Wesley, 1965,
pp. 151-154.
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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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