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An experimental investigation of the Mach number effect upon a normal shock wave — Tubulent boundary layer interaction on a curved wall

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Summary

The Mach number effect upon the normal shock wave — turbulent boundary interaction is investigated experimentally.

The measurements included flow parameters distribution determination, boundary layer development through the interaction area and the shock wave topography visualization. In order to have better insight into separation development the oil flow technique has been applied. The comparison of our results with other published data is presented.

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Authors and Affiliations

  1. Instytut Maszyn Przeplywowych PAN, ul. Gen. J. Fiszera 14, PL-80952, Gdańsk, Poland

    P. Doerffer

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  1. P. Doerffer
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With 10 Figures

The experiments have been carried out at the Institut für Strömungslehre und Strömungsmaschinen, Universität Karlsruhe, Federal Republic of Germany

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Doerffer, P. An experimental investigation of the Mach number effect upon a normal shock wave — Tubulent boundary layer interaction on a curved wall. Acta Mechanica 76, 35–51 (1989). https://doi.org/10.1007/BF01175795

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  • DOI: https://doi.org/10.1007/BF01175795

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