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Airfoil flow instabilities induced by background flow oscillations

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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.

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Authors and Affiliations

  1. Warsaw University of Technology ul. Nowowiejska 24, 00-665 Warszawa, Poland, , , , , , PL

    W. C. Selerowicz & A. P. Szumowski

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  1. W. C. Selerowicz
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  2. A. P. Szumowski
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Received: 6 June 2000 / Accepted: 18 October 2001

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Selerowicz, W., Szumowski, A. Airfoil flow instabilities induced by background flow oscillations. Experiments in Fluids 32, 441–446 (2002). https://doi.org/10.1007/s00348-001-0377-4

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  • DOI: https://doi.org/10.1007/s00348-001-0377-4

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