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Forced oscillations of airfoil flows

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Abstract

The effect of background flow oscillations on a 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 the expansion and compression waves generated at the plate, the flow over the airfoil flow was drastically disturbed. This resulted in the presence of high intensity oscillations of a shock wave and a separation bubble on the suction surface of the airfoil. For relatively large values of the airfoil angle of attack, weak shock waves (transonic sound waves) were periodically shed upstream of the airfoil.

This work was supported by Commission of the European Communities (Communit's Action for Cooperation in Science and Technology with Central and Eastern European Countries).

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Authors and Affiliations

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

    A. P. Szumowski

  2. Institut für Experimentelle Strömungsmechanik DLR, Bunsenstr. 10, D-37073, Göttingen, Germany

    G. E. A. Meier

Authors
  1. A. P. Szumowski
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  2. G. E. A. Meier
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Additional information

The authors wish to thank Mr P. Koperski for his effective assistance in taking the photographs.

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Szumowski, A.P., Meier, G.E.A. Forced oscillations of airfoil flows. Experiments in Fluids 21, 457–464 (1996). https://doi.org/10.1007/BF00189048

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  • DOI: https://doi.org/10.1007/BF00189048

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