A turbojet is flying with a velocity of 280 m/s at an altitude of 5,000 m, where ambient conditions are 50 kPa and -10°C. The compressor pressure ratio is 13,

and the temperature at the turbine inlet is 1300K. The mass flow rate of air entering the engine is 110 kg/s.Assume ideal operation of all components and constant specific heat (k=1.4). Include non ideal operation of the compressor, nozzle and turbine where: \eta_{C}=80, \eta_{T}=85 \text { and } \eta_{N}=90 (a) draw a schematic of the system (b) draw the process on a T-s diagram (c) determine the flight Mach number Using an ideal, air-standard analysis determine (d) the temperature and pressure at 1. the compressor inlet 2. the compressor exit 3. the turbine exit 4. the nozzle exit (assume Pe=pa) (e) the turbine pressure ratio (f) the power input to the compressor in hp (g) the velocity at the nozzle exit (h) the thrust produced