The thermal efficiency of an aircraft gas turbine engine (turbojet, based on ideal Brayton cycle) is 25%. The aircraft travels at a speed 770 km/h at an altitude 6800 m above sea level (standard atmospheric air). The combustion chamber outlet temperature is 1100 °C. Determine: (a) the pressure ratio of the engine (3 points), (b) the outlet temperature of the engine's compressor (4 points), (c) the exit velocity of the jet from the nozzle in m/s (5 points), and (d) the generated specific propulsive work in kJ/kg (3 points). Use constant specific heats at 250K, and k=1.4.