• An aircraft engine is fitted with a single-sided centrifugal compressor. The aircraft flies with a speed of 850 km/h at an altitude where the pressure is 0.23 bar and the temperature 217 K. The inlet duct of the impeller eye contains fixed vanes which give the air pre-whirl of 65◦ at all radii. These inner and out diameters of the eye are 180 and 330 mm respectively, the diameter of the impeller tip is 540 mm and the rotational speed 16000 rpm. Estimate the stagnation pressure at the compressor outlet when the mass flow is 216 kg per minute. Neglect losses in 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 the power input factor as 1.04.