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Experimental Investigation of Axisymmetric Transitional Shock Wave Boundary Layer Interactions at Mach 5

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29th International Symposium on Shock Waves 2 (ISSW 2013)

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Abstract

Shock Wave Boundary Layer Interactions (SWBLIs) can induce separation which causes loss of a control surface effectiveness, drop of an air intake efficiency and it may be the origin of large scale fluctuations such as air-intake buzz, buffeting or fluctuating side loads in separated propulsive nozzles. The subsequent reattachment of the separated shear layer on a nearby surface gives rise to local heat transfer rates which can be far in excess of those of an attached boundary layer [1].

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References

  1. Edney, B.: Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Aeronautical Research Institute of Sweden, FFA Report 115, Stockholm (1968)

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Author information

Authors and Affiliations

  1. AeroPhysics Lab, School of MACE, University of Manchester, Manchester, M13 9PL, UK

    E. Erdem & K. Kontis

  2. Fluid Gravity Engineering, The Old Coach House, 1 West Street, Emsworth, PO10 7DX, UK

    E. Johnstone

  3. European Space Research and Technology Centre, Postbus 299, Keplerlaan 1, 2200 AG, Noordwijk, The Netherlands

    N. Murray & J. Steelant

Authors
  1. E. Erdem
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  2. K. Kontis
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  3. E. Johnstone
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  4. N. Murray
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  5. J. Steelant
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Editor information

Editors and Affiliations

  1. Department of Engineering Physics, University of Wisconsin, Madison, USA

    Riccardo Bonazza

  2. Department of Mechanical Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA

    Devesh Ranjan

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© 2015 Springer International Publishing Switzerland

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Erdem, E., Kontis, K., Johnstone, E., Murray, N., Steelant, J. (2015). Experimental Investigation of Axisymmetric Transitional Shock Wave Boundary Layer Interactions at Mach 5. In: Bonazza, R., Ranjan, D. (eds) 29th International Symposium on Shock Waves 2. ISSW 2013. Springer, Cham. https://doi.org/10.1007/978-3-319-16838-8_65

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