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.