An aircraft engine is fitted with a single-sided centrifugal compressor. The aircraft flies with a speed of 230 m/s at an altitude where the pressure is 0.23 bar and temperature 217 K. The intake duct of the impeller eye contains fixed vanes which give the air prewhirl of 25o at all radii. The inner and outer diameters of the eye are 18cm and 33cm respectively, the diameter of the impeller peripheri is 54 cm and the rotational speed 270 rev/s. Estimate the stagnation pressure at the compressor outlet when the mass flow is 3.6 kg/s. Neglect losses in the inlet duct and fixed vanes and assume that the isentropic efficiency of the compressor is 0.80. Take the slip factor as 0.9 and power input factor as 1.04.