A turboprop engine operates at an altitude of 3000 meters above mean sea level and an aircraft speed of 525 kmph. The data for the engine is given below: = 0.875 = 0.790 Inlet diffuser efficiency Compressor efficiency Velocity of air at compressor entry = 90 m/s Temperature rise through the compressor= 230C Properties of air: y = 1.4, cp = 1.005 kJ/kg K From the above data calculate (a) pressure rise through the inlet diffuser (b) pressure ratio developed by the compressor (c) power required by the compressor per unit flow rate of air and (d) the air standard efficiency of the engine.