Consider a turbojet engine flying in air at Ta-250 K, Pa-50 kPa and at a velocity of 250 m/s. The inlet area of the diffuser is 0.15 m2. At the exit of the diffuser, the pressure and temperature are 60 kPa and 265 K, respectively. The compressor has a pressure ratio of 12 and an isentropic efficiency of 85%. The turbine has an isentropic efficiency of 90% and exits to a pressure of 150 kPa. The nozzle has an isentropic efficiency of 95%. The required thrust is 4000 N. Use EES to assess the following: a) The mass flow rate through the engine. b) The exit velocity (Vi) of the diffuser. c) The exit area (Ai) of the diffuser. d) Isentropic conditions (Tis and Vis) at the exit of the diffuser. he isentropic efficiency of the diffuser. f The compressor power requirements. g) If 12 MW of thermal energy is added in the way of heat at the combustor (i. e. the high temperature heat exchanger), determine the exit temperature (T) and exit pressure (P3) of the combustor. h) Determine the back-work ratio. i) Determine the temperature at the exit of the nozzle (Ts). j) Determine the exit area (As) of the nozzle.