Path: Propulsion/Gas
% Computes the area ratio from Mach Number.
Type AreaRatioFromMach for a demo.
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Form:
M = AreaRatioFromMach( aR, 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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aR (1,:) Area ratio Exit Area/Throat Area
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References: Hill, P.G., Peterson, C. R., "The Mechanics and
Thermodynamics of Propulsion," Addison-Wesley Publishing
Company, 1970, p. 49.
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Common: Graphics/Plot2D
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