Supercritical Cascade Flow Analysis With Shock-Boundary Layer Interaction and Shock-Free Redesign

[+] Author and Article Information
P. Niederdrenk, H. Sobieczky

Institute for Theoretical Fluid Mechanics, DFVLR, Göttingen, Federal Republic of Germany

G. S. Dulikravich

Department of Aerospace Engineering, Pennsylvania State University, University Park, PA

J. Turbomach 109(3), 413-419 (Jul 01, 1987) (7 pages) doi:10.1115/1.3262121 History: Received November 07, 1984; Online November 09, 2009


This paper describes improvements made in a user-oriented analysis code for steady two-dimensional transonic flows in turbomachinery cascades. The full potential equation is solved by a finite area technique, using a C -type grid and an analytical wake model. Solution adaptive grid clustering refines the inviscid computationally captured shock. The boundary layer is computed by an integral method except in the shock region, where the analytical interaction model of Bohning and Zierep smoothes out the pressure distribution on the airfoil surface. The code is applied in its analysis and design modes to an experimentally tested cascade of airfoils.

Copyright © 1987 by ASME
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