Engineering, 09.11.2019 03:31 ygrant03

The reservoir pressure and temperature for a convergent-divergent nozzle are 5 atm and 15 0c, respectively. the airflow is expanded isentropically to supersonic speed at the nozzle exit. if the exit to throat area ratio is 2.193, calculate the following air properties at the exit: mach number, pressure, temperature, density, velocity, total pressure, total temperature.

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The reservoir pressure and temperature for a convergent-divergent nozzle are 5 atm and 15 0c, respec...