Self-Excited Oscillation of Transonic Flow Around an Airfoil in Two-Dimensional Channels

[+] Author and Article Information
K. Yamamoto

Aeroengine Division, National Aerospace Laboratory, Chofu, Tokyo, Japan

Y. Tanida

Research Center for Advanced Science and Technology, University of Tokyo, Tokyo, Japan

J. Turbomach 112(4), 723-731 (Oct 01, 1990) (9 pages) doi:10.1115/1.2927715 History: Received January 04, 1989; Online June 09, 2008


A self-excited oscillation of transonic flow in a simplified cascade model was investigated experimentally, theoretically and numerically. The measurements of the shock wave and wake motions, and the unsteady static pressure field predict a closed-loop mechanism, in which the pressure disturbance that is generated by the oscillation of boundary layer separation propagates upstream in the main flow and forces the shock wave to oscillate, and then the shock oscillation disturbs the boundary layer separation again. A one-dimensional analysis confirms that the self-excited oscillation occurs in the proposed mechanism. Finally, a numerical simulation of the Navier–Stokes equations reveals the unsteady flow structure of the reversed flow region around the trailing edge, which induces the large flow separation to bring about the antiphase oscillation.

Copyright © 1990 by The American Society of Mechanical Engineers
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