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Turbulent Shear-Layer/Shock-Wave Interactions pp 247–258Cite as

Separation ahead of Blunt Fins in Supersonic Turbulent Boundary-Layers

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Part of the book series: International Union of Theoretical and Applied Mechanics ((MANUTECH))

Summary

An experimental study of the three dimensional shock wave/turbulent boundary layer interaction induced by a blunt fin was made mainly at Mach 2.48. The effects of leading edge shape and angle of attack were studied. Surface pressure measurements, and flow visualizations were made. The results show that, on the test surface near the fin, the structure of the vortex in the reverse flow region depends strongly on the leading edge shape, but it does not affect the flow near the separation point. Furthermore the effects of the angle of attack appear downstream of the plateau region especially on the windward side.

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References

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Author information

Authors and Affiliations

  1. Department of Mechanical Engineering Collegé of Science and Engineering, Aoyama Gakuin University, Tokyo 157, Japan

    N. Saida

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  1. N. Saida
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Editor information

Editors and Affiliations

  1. Direction de L’Aérodynamique, ONERA, B.P. 72, 29. Av. de la Division Leclerc, F-92322, Châtillon Cedex, France

    J. Délery

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© 1986 Springer-Verlag Berlin, Heidelberg

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Saida, N. (1986). Separation ahead of Blunt Fins in Supersonic Turbulent Boundary-Layers. In: Délery, J. (eds) Turbulent Shear-Layer/Shock-Wave Interactions. International Union of Theoretical and Applied Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-82770-9_20

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  • DOI: https://doi.org/10.1007/978-3-642-82770-9_20

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-82772-3

  • Online ISBN: 978-3-642-82770-9

  • eBook Packages: Springer Book Archive

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