Abstract
A numerical method is proposed for analysing the transonic flows through an arbitrary shaped cascade on an arbitrary surface of revolution. The method which is an improvement of the streamline curvature method developed by Katsanis and Wilkinson needs very short computer time and has practically sufficient accuracy. The method is applicable to the flow conditions which considerably deviate from the shockless entry, to the transonic flows with locally supersonic regions and without shock wave, and to the blades which do not have large radius of curvature at the leading edge. As numerical examples, the pressure distributions on the blade surface, the streamlines, and the contours of Mach number for compressor and turbine cascades are calculated. The pressure distributions agree well with the previous experimental and numerical results.
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