2. Calculate the mass flow and the annulus area at the rotor outlet for an axial compressor stage. The flow enters the rotor without swirl, at a Mach number of 0.4, at a stagnation pressure of 200 kPa and a stagnation temperature of 370 K, in an annulus of area 0.17 m. The axial velocity is constant across the rotor, but the flow leaves at 30.6 degrees to the axial direction. The stagnation pressure at the rotor outlet is 230 kPa and the stagnation to stagnation polytropic efficiency to this point is 0.94. Use properties of air as k=1.4and Cp= 1008.9 J/Kg K