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An experimental investigation of hypervelocity flow in a conical nozzle

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Abstract

The flow in a conical nozzle is examined experimentally for a range of hypervelocity conditions in a free-piston shock tunnel. The pitot pressure levels compare reasonably well with an inviscid numerical prediction which includes a correction for the growth of the nozzle wall boundary layer. The size of the nozzle wall boundary layer seems to be well predicted by semi-empirical expressions developed for perfect gas flows, as do data from other free-piston shock tunnels.

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Author notes

  1. S. G. Mallinson

    Present address: Department of Aeronautics, Imperial College of Science, Technology and Medicine, Prince Consort Road, SW7 2BY, London, UK

Authors and Affiliations

  1. Department of Aerospace and Mechanical Engineering, University College, University of New South Wales, Australian Defence Force Academy, 2600, Canberra, ACT, Australia

    S. G. Mallinson, S. L. Gai & N. R. Mudford

Authors
  1. S. G. Mallinson
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  2. S. L. Gai
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  3. N. R. Mudford
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Mallinson, S.G., Gai, S.L. & Mudford, N.R. An experimental investigation of hypervelocity flow in a conical nozzle. Appl. Sci. Res. 57, 81–93 (1996). https://doi.org/10.1007/BF02528765

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  • DOI: https://doi.org/10.1007/BF02528765

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