Air at a pressure of 350 kPa, a temperature of 80°C, and avelocity of 180 m/s enters a convergent–divergent nozzle. A normalshock occurs in the nozzle at a location where the Mach number is2. If the air mass flow rate through the nozzle is 0.7 kg/s, and ifthe pressure on the nozzle exit plane is 260 kPa, find the nozzlethroat area, the nozzle exit area, the temperatures upstream anddownstream of the shock wave, and the change in entropy through thenozzle.
