Find exit pressure and temperature for supersonic exit flow

Reference no: EM131238499

Find the exit pressure and temperature for supersonic exit flow to exist in the nozzle flow of Problem 15.47.

Problem 15.47

An air flow at 600 kPa, 600 K, M = 0.3 flows into a convergent-divergent nozzle with M = 1 at the throat. Assume a reversible flow with an exit area twice the throat area and find the exit pressure and temperature for subsonic exit flow to exist.

Reference no: EM131238499

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