The nozzle in the power plant of a supersonic aircraft is designed to function under isentropic conditions at a cruising altitude of 65000 ft (20 km) where the ambient pressure is 5.5 kPa. The jet of combusted gas exits the nozzle at Mach 3 relative to the aircraft at isentropic supersonic conditions (no expansion waves) at the cruising altitude. The aircraft changes altitude to 35000 ft (10 km) where the ambient pressure is 26.5 kPa. Under what conditions will the nozzle operate at this altitude i. e. will there be a normal shock, oblique shock, isentropic flow or expansion waves? Explain. Assume that the chamber (reservoir) conditions remain the same and that the properties of exhaust gas and air are same.