Question
Air is flowing through a nozzle, from a reservoir with pressure of 600 kPa and temperature...
Air is flowing through a nozzle, from a reservoir with pressure of 600 kPa and temperature of 350 K, with supersonic flow downstream of the throat. A shock occurs in the expanding part of the nozzle where the nozzle area is 9 times larger than the throat area. What is the pressure immediately downstream of the shock, in kilopascals?
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