Air at a pressure of 350 kPa, a temperature of 80°C, and a
velocity of 180 m/s enters a convergent–divergent nozzle. A normal
shock occurs in the nozzle at a location where the Mach number is
2. If the air mass flow rate through the nozzle is 0.7 kg/s, and if
the pressure on the nozzle exit plane is 260 kPa, find the nozzle
throat area, the nozzle exit area, the temperatures upstream and
downstream of the shock wave, and...