If the Mach number at the nozzle exit is 3, calculate the exit pressure, temperature, and density.
1. Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure, temperature, and density. 2. Consider a supersonic nozzle across which the pressure ratio is p.fp0 = 0.2. Calculate the ratio of exit area to throat area.
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