Determine the throat area and the exit mach number

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Reference no: EM13704059

Air flows isentropic ally at the rate of 1 kg/s through a converging-diverging nozzle. The stagnation temperature is 310 K and the stagnation pressure is 810 kPa. If the exit pressure is 101.3 kPa, determine:

a) The throat area.

b) The exit Mach number.

c) The exit velocity.

Reference no: EM13704059

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Determine the throat area and the exit mach number : Air flows isentropic ally at the rate of 1 kg/s through a converging-diverging nozzle. The stagnation temperature is 310 K and the stagnation pressure is 810 kPa. If the exit pressure is 101.3 kPa, determine: The throat area. The exit Mach number.

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