Air flows isentropic ally at the rate of 0.5 kg/s through a supersonic convergent-divergent nozzle. At the inlet, the pressure is 680 kPa. the temperature 295 K. and the area is 6.5cm^2. If the exit area is 13 cm*2, calculate:
a) The Stagnation pressure and temperature.
b) The exit Mach number
c) The exit pressure and Temperature
d) The area and the verlocity at the throat.