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SBLI control for wings and inlets

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Book cover Shock Waves

The application of flow control to shock wave / boundary layer interactions (SBLIs) has been widely studied in recent decades. Two important practical applications for shock control technology are transonic wings (Fig. 1) and supersonic engine inlets (Fig. 2). In both cases the overall performance is significantly affected by shock wave / boundary layer interactions and it is hoped that flow control can provide considerable benefits.

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Authors and Affiliations

  1. Department of Engineering, University of Cambridge, Trumpington St.,, Cambridge, CB2 1PZ, United Kingdom

    H. Babinsky & H. Ogawa

Authors
  1. H. Babinsky
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  2. H. Ogawa
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Editor information

Editors and Affiliations

  1. German Aerospace Center, DLR, Bunsenstraße 10, 37073 Göttingen, Germany

    Klaus Hannemann

  2. French-German Research Institute of Saint Louis, ISL, 5 rue du Général Cassagnou, 68301 Saint-Louis, France

    Friedrich Seiler

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© 2009 Springer-Verlag Berlin Heidelberg

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Babinsky, H., Ogawa, H. (2009). SBLI control for wings and inlets. In: Hannemann, K., Seiler, F. (eds) Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-85168-4_7

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  • DOI: https://doi.org/10.1007/978-3-540-85168-4_7

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-540-85167-7

  • Online ISBN: 978-3-540-85168-4

  • eBook Packages: EngineeringEngineering (R0)

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