Consider a turbojet engine in flight. at entry, air is at 230 k, 26 kpa & 220 m/s. the compressor pressure ratio is 11, whereas the mass flow rate of air is 25 kg/s. air exits the nozzle at 26 kpa, and the turbine inlet temperature is 1400 k. compressor and turbine have isentropic efficiencies of 85% and 90%, respectively, whereas diffuser and nozzle processes are isentropic. pressure drop for flow through the combustor is negligible. except at the diffuser inlet and nozzle exit, kinetic energy is negligible everywhere else. on the basis of air-standard analysis, determine: (a) pressures (kpa) and temperatures (k) at each principal state. (b) rate of heat addition (kj/s) to air, when passing through the combustor. (c) velocity at nozzle exit (m/s).