Air at 26 kPa, 230 K, and 220 rn/s enters a turbojet engine in flight. The air mass flow rate is 25 kg/s. The compressor pressure ratio is 11, the turbine inlet temperature is 1400 K, and air exits the nozzle 26 kPa. The diffuser and the nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 85% and 90%, respectively. There is no pressure drop for flow through the combustor. Kinetic energy is negligible everywhere except at the diffuser inlet and the nozzle exit. On the basis of air-standard analysis, determine: (a) the pressures and temperatures at each state, (b) the rate of heat addition to the air passing through the combustor, (c) the velocity at the nozzle exit.