Ajet airplane is flying at 30,000 ft altitude at airspeed v0 = 825 ft/s. the ambient (freestream) conditions are p0 = 628.4 psf and t0 = 411.7 deg r. air enters the diffuser of a turbojet engine and then passes through the compressor. a temperature sensor at the diffuser entrance (station 1) tells us that the static temperature is t1 = 435 deg r. flow through the diffuser and compressor is adiabatic and frictionless. the inlet area (diffuser entrance) is a1 = 2 ft2 . the compressor raises the total pressure so that pt3/pt2 = 15.a) compute the airplane’s flight mach number (m0) and the mach number at the diffuser entrance, m1.b) compute the stagnation (total) temperatures at the entrance to the diffuser (station 1), entrance to the compressor (station 2), and exit of the compressor (station 3).c) compute the mass-flow rate through the diffuser and compressor.