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Experiments in Fluids

, Volume 32, Issue 4, pp 441–446 | Cite as

Airfoil flow instabilities induced by background flow oscillations

  • W. C. Selerowicz
  • A. P. Szumowski

Abstract

 The effect of background flow oscillations on transonic airfoil (NACA 0012) flow was investigated experimentally. The oscillations were generated by means of a rotating plate placed downstream of the airfoil. Owing to oscillating chocking of the flow caused by the plate, the airfoil flow periodically accelerated and decelerated. This led to strong variations in the surface pressure and the airfoil loading. The results are presented for two angles of attack, α=4° and α=8.5°, which correspond to the attached and separated steady airfoil flows, respectively.

Keywords

Surface Pressure Strong Variation Flow Instability Flow Oscillation Background Flow 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2002

Authors and Affiliations

  • W. C. Selerowicz
    • 1
  • A. P. Szumowski
    • 1
  1. 1.Warsaw University of Technology ul. Nowowiejska 24, 00-665 Warszawa, PolandPL

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