Path: Propulsion/Gas
% Computes the Mach number from area ratio. The throat is at Mach 1.
Type MachFromAreaRatio for a demo.
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Form:
M = MachFromAreaRatio( aR, gamma )
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Inputs
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aR (1,1) Area ratio Exit Area/Throat Area
gamma (1,1) Ratio of specific heats
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Outputs
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M (1,1) Mach number
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References: Hill, P.G., Peterson, C. R., "The Mechanics and
Thermodynamics of Propulsion," Addison-Wesley Publishing
Company, 1970, p. 221.
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Propulsion: Gas/AreaRatioFromMach Math: Solvers/Secant
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