A converging/diverging 2-D supersonic nozzle discharging to the atmosphere is designed to achieve Mach=1.5 under ideally expanded conditions. Converging/diverging nozzle is attached to a plenum chamber with a total pressure, P0 and a total temperature, T0. Assume the atmospheric pressure is, Patm = 100,000 Pa abs. Use R=287 J/(kg . K), = 1.4, Cp = 1004.5 J/(kg . K).

a-Calculate the total pressure, P0 required to operate the nozzle under ideally expanded conditions.

b- If the total pressure in the plenum chamber is increased to P0 new = 2.15 P0, 2.15 times the total pressure calculated in part a), calculate the nozzle exit static pressure and the flow turning angle as the flow exits the nozzle.

c- If the total pressure in the plenum chamber is decreased to P0 new = P0/4, 1/4th of the total pressure calculated in part a), calculate the nozzle exit Mach number. Discuss if there is a normal shock in the nozzle or not