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Vortex Dynamics of Delta Wings

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Frontiers in Experimental Fluid Mechanics

Part of the book series: Lecture Notes in Engineering ((LNENG,volume 46))

Abstract

The typical angle of attack for maximum lift of a delta wing is about 35°, which is much higher than for a two-dimensional airfoil. The delta wing is, therefore, suitable for highly maneuverable aircraft. In this paper, experimental results for delta wings is reviewed. The review is made from the perspective of fundamental fluid dynamic mechanisms. In particular, the balance between vorticity generation on the surface and freestream convection of it is used to understand how different parameters affect the leading edge vortices which dominate the aerodynamics of a delta wing at high angles of attack.

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Author information

Authors and Affiliations

  1. Department of Aerospace Engineering, University of Southern California, Los Angeles, California, 90089-1191, USA

    Mario Lee & Chih-Ming Ho

Authors
  1. Mario Lee
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  2. Chih-Ming Ho
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Editors and Affiliations

  1. Department of Aerospace and Mechanical Engineering, University of Notre Dame, 46556, Notre Dame, IN, USA

    Mohamed Gad-el-Hak

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© 1989 Springer-Verlag Berlin, Heidelberg

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Lee, M., Ho, CM. (1989). Vortex Dynamics of Delta Wings. In: Gad-el-Hak, M. (eds) Frontiers in Experimental Fluid Mechanics. Lecture Notes in Engineering, vol 46. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-83831-6_8

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  • DOI: https://doi.org/10.1007/978-3-642-83831-6_8

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-540-51296-7

  • Online ISBN: 978-3-642-83831-6

  • eBook Packages: Springer Book Archive

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