A jet plane cruises at a speed of 980 km/hr. air enters the turbojet engines at 0.73 bar, 230 k. the pressure ratio across the compressor is 10 and the turbine inlet temperature is 1650 k. the diameter of the engine is 1.2 m. using typical assumptions for all the components and 100% component effeciencies, determine:
a) the mass flow rate of air
b) the specific enthalpies at the entrance and exit of all the components
c) the exit velocity of the gases.
d) the heat supplied by the fuel
e) the thrust of the engine