Air at 22 kPa, 220 K, and 250 m/s enters a turbojet engine in flight at an altitude of 10000m. The pressure ratio across the compressor is 12. Turbine inlet temperature is 1400K, and the pressure at the nozzle exit is 22 kPa. The compressor and turbine have isentropic efficiencies of 85% and 88% respectively, and there is no significant drop in pressure for flow through the combustor. On the bases of air standard analysis considering the variation of specific heats, determine: pressures and temperatures at each principle state, and the velocity at the nozzle exit.