Consider a converging-diverging nozzle with a throat area of 0.0015 and exit area of 0.002 . The stagnation pressure is 600 kPa and stagnation temperature is 10 a) When there is shock at section S having an area of 0.0018 , find the pressure and Mach number after the shock and at the exit. b) When there is no shock and the exit pressure is 580 kPa, find the velocity and Mach number at the throat.