Air at 25 kPa and 230 K enters a turbojet engine with a velocity of 250 m/sec. The pressure ratio across the compressor is 12. The turbine inlet temperature is 1400 K and the pressure at the nozzle exit is 25 kPa. The diffuser, compressor, turbine and nozzle processes are isentropic and there is no pressure drop for flow through the combustor. Under steady state operating conditions, determine (i) the velocity at the nozzle exit, and (ii) the pressures & temperatures at each state. State the assumptions made. Draw the line diagram indicating all the components & show the processes on a T–s diagram.