A semi-analytical method of predicting losses and deviation angle for an arbitrary straight compressor cascade has been derived. The method has been developed at SVU´SS and is based upon the solution of the direct cascade problem using the following sources: (i) a potential flow calculation; (ii) attached boundary layer techniques; and (iii) experimental cascade data for separated flow. As an example of an application of the method, simple relations between geometric and aerodynamic cascade parameters have been derived by doing a systematic set of calculations for about 100 cascade configurations which had a 65-series blade profile and were run at low speed. The derived semi-analytical correlation has been compared to the published semi-empirical method of NASA for 65-series aerofoils, to experiments on cascades, and to results from a low-speed compressor.

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