Air expands from a storage tank through a converging-diverging nozzle. Under certain conditions, it is found that a normal shock exists in the diverging section of the nozzle at an area equal to twice the throat area, with the exit area of the nozzle equal to four times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with a constant y = 1.4, and that the storage tank pressure and temperature are 400 kPa and 500 K, determine the following:
a) A* for flow from inlet to shock
b) A* for flow from shock to exit
c) Mach number at nozzle exit plane
d) Stagnation pressure at nozzle exit plane
e) Exit plane static pressure
f) Exit plane velocity