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RESEARCH PAPERS

Viscous Flow in a Controlled Diffusion Compressor Cascade With Increasing Incidence

[+] Author and Article Information
Y. Elazar, R. P. Shreeve

Turbopropulsion Laboratory, Department of Aeronautics and Astronautics, Naval Postgraduate School, Monterey, CA 93943

J. Turbomach 112(2), 256-265 (Apr 01, 1990) (10 pages) doi:10.1115/1.2927642 History: Received January 17, 1989; Online June 09, 2008

Abstract

A detailed two-component LDV mapping of the flow through a controlled diffusion compressor cascade at low Mach number ( ~ 0.25) and Reynolds number of about 7 × 105 , at three inlet air angles from design to near stall, is reported. It was found that the suction-side boundary layer reattached turbulent after a laminar separation bubble, and remained attached to the trailing edge even at the highest incidence, at which losses were 3 to 4 times the minimum value for the geometry. Boundary layer thickness increased to fill 20 percent of the blade passage at the highest incidence. Results for pressure-side boundary layer and near-wake also are summarized. Information sufficient to allow preliminary assessment of viscous codes is tabulated.

Copyright © 1990 by The American Society of Mechanical Engineers
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