A stationary normal shock stands in the diverging section of a converging- diverging nozzle. The Mach number ahead of the shock is 3.2. The nozzle area at the shock is 550 mm. The nozzle is fed from a large tank where the pressure is 1100 kPa (gage) and the temperature is 420 K. (a) Find the Mach number, stagnation pressure, and static pressure after the shock. (b) Calculate the nozzle throat area. (c) If the nozzle exit area is 620 mm, estimate the exit Mach number. 1080)