Find mach number at throat and mass flow rate through nozzle


A converging diverging nozzle undergoes isentropic flow. Stagnation pressure and stagnation temperature is 500 kpa and 1000k. Ae=0.02m^2. The exit pressure is 100 kpa. what is the mach number at the throat and the mass flow rate through the nozzle.

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Mechanical Engineering: Find mach number at throat and mass flow rate through nozzle
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