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Self-Excited Oscillation of Transonic Flow Around an Airfoil in Two-Dimensional Channel PUBLIC ACCESS

[+] Author Affiliations
Kazuomi Yamamoto

National Aerospace Laboratory, Chofu, Tokyo, Japan

Yoshimichi Tanida

University of Tokyo, Tokyo, Japan

Paper No. 89-GT-58, pp. V001T01A030; 10 pages
doi:10.1115/89-GT-58
From:
  • ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Toronto, Ontario, Canada, June 4–8, 1989
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7913-9
  • Copyright © 1989 by ASME

abstract

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 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 anti-phase oscillation.

Copyright © 1989 by ASME
This article is only available in the PDF format.

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