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RESEARCH PAPERS

Oscillating Cascade Aerodynamics at Large Mean Incidence

[+] Author and Article Information
D. H. Buffum

NASA Lewis Research Center Cleveland, OH 44135

V. R. Capece, A. J. King

Department of Mechanical & Aeronautical Engineering, University of California, Davis, CA 95616

Y. M. EL-Aini

Pratt & Whitney, West Palm Beach, FL 33410

J. Turbomach 120(1), 122-130 (Jan 01, 1998) (9 pages) doi:10.1115/1.2841373 History: Received February 01, 1996; Online January 29, 2008

Abstract

The aerodynamics of a cascade of airfoils oscillating in torsion about the midchord is investigated experimentally at a large mean incidence angle and, for reference, at a low mean incidence angle. The airfoil section is representative of a modern, low-aspect-ratio, fan blade tip section. Time-dependent airfoil surface pressure measurements were made for reduced frequencies of up to 1.2 for out-of-phase oscillations at a Mach number of 0.5 and chordal incidence angles of 0 and 10 deg; the Reynolds number was 0.9 × 106 . For the 10 deg chordal incidence angle, a separation bubble formed at the leading edge of the suction surface. The separated flow field was found to have a dramatic effect on the chordwise distribution of the unsteady pressure. In this region, substantial deviations from the attached flow data were found, with the deviations becoming less apparent in the aft region of the airfoil for all reduced frequencies. In particular, near the leading edge the separated flow had a strong destabilizing influence while the attached flow had a strong stabilizing influence.

Copyright © 1998 by The American Society of Mechanical Engineers
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