A turbojet aircraft is flying with a velocity of 320 m/s at an altitude of 9150 m, where the ambient conditions are 32 kPa and -32 degrees C. The pressure ratio across the compressor is 12, and th etemperature at the turbine inlet is 1400K. Air enters teh compressor at a rate of 60 kg/s, and the jet fuel has a heating value of 42,700 kj/kg. Assuming ideal operation for all components and constant specific heats for air at room temperature, determine (a) the velocity of the exhaust gases, (b) the propulsion power developed, and (c) the rate of fuel consumption.