Calculate compressible flow ratios and gas properties for isentropic and isothermal flow (critical over stagnation ratios, flowing over stagnation ratios, and flowing over critical flow ratios).
For isentropic flow, critical flow occurs at M = 1. For isothermal flow, critical flow occurs at M = 1 / √k, where k is the specific heat ratio (Cp/Cv). For isothermal flow the isothermal temperature is assumed equal to the stagnation temperature. Phase changes are ignored.
For flow through a throat, the flow upstream from the throat is sub critical (M ≤ Mc). The flow downstream is super critical (M > Mc). The area ratio is inversely proportional to the mass flux ratio. At stagnation conditions, the area ratio is infinite.
Use the Result Plot option to plot flow ratios versus Mach number, or nozzle area ratio and diameter ratio versus Mach number.
Reference : Fluid Mechanics, Frank M White, McGraw Hill
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