Aturboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. the turbine drives a propeller as well as the compressor, delivering a net power of 1.10 mw to the propeller. air enters the diffuser at 8000 m altitude (ta = 236k, pa = 36 kpa) with a velocity of 550 km/h, and decelerates essentially to zero velocity. the compressor pressure ratio is 7.3 and the compressor has an isentropic efficiency of 83%. the turbine inlet temperature is 1360 k, and its isentropic efficiency is 86%. the turbine exit pressure is 10 kpa higher than the ambient pressure at that altitude. flow through the diffuser and nozzle is isentropic. neglect kinetic energy except at the diffuser inlet and the nozzle exit. using an air-standard analysis, determine: a) the mass and volumetric flow rates entering the diffuser, in kg/s and m3/s, respectively. b) the rate of heat addition to the combustor, in mw. c) the velocity at the nozzle exit, in m/s.