Solution of Plane Cascade Flow Using Improved Surface Singularity Methods

[+] Author and Article Information
E. R. McFarland

NASA Lewis Research Center, Cleveland, Ohio

J. Eng. Power 104(3), 668-674 (Jul 01, 1982) (7 pages) doi:10.1115/1.3227330 History: Received December 18, 1980; Online September 28, 2009


A solution method has been developed for calculating compressible inviscid flow through a linear cascade of arbitrary blade shapes. The method uses advanced surface singularity formulations which were adapted from those found in current external flow analyses. The resulting solution technique provides a fast flexible calculation for flows through turbomachinery blade rows. The solution method and some examples of the method’s capabilities are presented.

Copyright © 1982 by ASME
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