Air at 30 kPa, 250 K and 250 m/s enters a turbojet engine in flight at an

Question:

Air at 30 kPa, 250 K and 250 m/s enters a turbojet engine in flight at an altitude of 10,000 m. The pressure ratio across the compressor is 12. The turbine inlet temperature is 1400 K, and the pressure at the nozzle exit is 30 kPa. The diffuser and nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 85% and 80%, respectively, and there is no pressure drop for flow through the combustor. Using the IG model, determine (a) the velocity (V) of the exhaust gases.