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Computational and experimental study of supersonic flow over axisymmetric cavities

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Abstract

Laminar and turbulent computations are presented for annular rectangular-section cavities, on a body of revolution, in a Mach 2.2 flow. Unsteady ‘open cavity flows’ result for all laminar computations for all cavity length-to-depth ratios, L/D (1.33, 10.33, 11.33 and 12.33). The turbulent computations produce ‘closed cavity flows’ for L/D of 11.33 and 12.33. Surface pressure fluctuations at the front corner of the L/D = 1.33 cavity are periodic in some cases depending on the cavity length and depth, the boundary layer at the cavity front lip and the cavity scale. The turbulent computations are supported by experimental schlieren images, obtained using a spark light source, and time-averaged surface pressure data.

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Author notes

  1. K. Mohri

    Present address: Institute for Combustion and Gasdynamics, University of Duisburg-Essen, Essen, Germany

Authors and Affiliations

  1. Department of Aeronautics, Imperial College London, London, UK

    K. Mohri & R. Hillier

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  1. K. Mohri
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  2. R. Hillier
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Correspondence to K. Mohri.

Additional information

Communicated by F. Seiler.

This paper was based on work that was presented at the 26th International Symposium on Shock Waves, Goettingen, Germany, July 15–20, 2007.

K. Mohri was awarded with the ISWI (The International Shock Wave Institute) Student Award for the best student presentation at the Symposium.

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Mohri, K., Hillier, R. Computational and experimental study of supersonic flow over axisymmetric cavities. Shock Waves 21, 175–191 (2011). https://doi.org/10.1007/s00193-011-0312-4

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  • DOI: https://doi.org/10.1007/s00193-011-0312-4

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