At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pressure is 300 kpa, and the stagnation temperature is 600 k. at exit the stagnation pressure is 285 kpa and the static pressure 270 kpa. using compressible flow analysis, determine (i) the static temperature, static pressure, and mach number at inlet and the diffuser efficiency; (ii) the mach number at exit and entry. for air take γ = 1.376 and r = 287 j/(kg k).