Find the pressure-temperature and mach number at the exit

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Reference no: EM13712617

An air nozzle has an exit area 1.6 times the throat area. If a normal shock occurs at a plane where the area is 1.2 times the throat area, find the pressure, temperature, and Mach number at the exit. The stagnation temperature and pressure before the shock are 310K and 700KPa.

Reference no: EM13712617

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