Find the nozzle throat area the mach numbers before and

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Reference no: EM13612201

Air flows through a convergent-divergent nozzle from a large reservoir in which the pressure and temperature are maintained at 700 kPa and 60 C, respectively. The rate of air flow through the nozzle is 1 kg/s. On the exit plane of the nozzle the stagnation pressure is 550 kPa and the static pressure is 500 kPa. A shock wave occurs in the nozzle and the flow can be assumed to be isentropic everywhere except through the shock wave. Find the nozzle throat area, the Mach numbers before and after the shock, the nozzle areas at the point where the shock occurs and on the exit plane, and the air density on the exit plane of the nozzle.

Reference no: EM13612201

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