Discuss the below:
Q: At a point upstream of the throat of a converging-diverging nozzle, the properties are V1 = 200 m/s, T1 = 300 K, and p1 = 125 kPa. If the exit flow is supersonic, compute, from isentropic theory,
(a) M; and
(b) A1. The throat area is 35 cm2.