Atmospheric air enters the intake diffuser of a jet aircraft flying at a mach number of 0.8 at a constant altitude where the static pressure and temperature are 25kpa and 220k, respectively. the entrance area of the intake is 0.5m2 and the area at entry to the compressor is 0.8 m2. there is a loss of 10% of the stagnation pressure of the air as it flows to the compressor. using compressible flow theory and assuming adiabatic flow in the intake, determine the mach number and velocity of the flow entering the compressor.