Engineering, 22.04.2020 21:39, zachisthequeen2002

Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25 m2, respectively. The inlet reservoir pressure is 1 atm and the exit static pressure is 0.6 atm. For this pressure ratio, the flow will be supersonic in a portion of the nozzle, terminating with a normal shock inside of the nozzle. Calculate the local area ratio (A/A*) at which the shock is located inside the nozzle.

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Consider a convergent-divergent duct with exit and throat areas of 0.5 m2 and 0.25 m2, respectively....