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Slender Wings with Leading Edge Vortex-Separation

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Recent Contributions to Fluid Mechanics

Summary

The demands of high speed performance and maneuverability on modern transport- and fighter-aircraft require slender wings, whose leading edge vortex flows result in increased lift at high angle-of-attack. Beginning with the experimental and theoretical development and the history of application the article will discuss the application of panel- and vortex-lattice-methods and the latest employment of an Euler-code to predict the behaviour of the wing-vortex-system. Additionally the vortex-breakdown-phenomenon will be discussed.

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Author information

Authors and Affiliations

  1. Theoretical Aerodynamics Dept., Dornier GmbH, Postfach 1420, 7990, Friedrichshafen, Germany

    Stephan M. Hitzel

Authors
  1. Stephan M. Hitzel
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Editor information

Editors and Affiliations

  1. Dornier GmbH, D-7990, Friedrichshafen 1, Germany

    Werner Haase

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© 1982 Springer-Verlag Berlin Heidelberg

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Hitzel, S.M. (1982). Slender Wings with Leading Edge Vortex-Separation. In: Haase, W. (eds) Recent Contributions to Fluid Mechanics. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-81932-2_15

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  • DOI: https://doi.org/10.1007/978-3-642-81932-2_15

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-81934-6

  • Online ISBN: 978-3-642-81932-2

  • eBook Packages: Springer Book Archive

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