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Finite Volume 3DNS and PNS Solutions of Hypersonic Viscous Flow Around a Delta Wing using Osher’s Flux Difference Splitting

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Hypersonic Flows for Reentry Problems

Abstract

The Osher’s flux difference splitting scheme has been applied to the finite volume formulation of the three dimensional Navier-Stokes equations and the parabolized Navier-Stokes equations. Results for the hypersonic laminar flow around the blunt leading edge delta wing at an angle of attack of 30 degrees, i.e. Problem 7.1.2., are presented and discussed.

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Authors and Affiliations

  1. Department of Aerospace Engineering, University of Glasgow, Glasgow, G12 8QQ, UK

    N. Qin & B. E. Richards

Authors
  1. N. Qin
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  2. B. E. Richards
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Editor information

Editors and Affiliations

  1. Centre de Sophia Antipolis, INRIA, 2004 Route des Lucioles, F-06561, Valbonne Cedex, France

    Jean-Antoine Désidéri

  2. Department of Mathematics, University of Houston, Texas, 4800 Calhoun Road, University Park, 77004, Houston, TX, USA

    Roland Glowinski

  3. Aerodynamics Department, Dassault Aviation, 78 Quai Marcel Dassault, F-92214, Saint Cloud, France

    Jacques Périaux

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© 1991 Springer-Verlag Berlin Heidelberg

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Qin, N., Richards, B.E. (1991). Finite Volume 3DNS and PNS Solutions of Hypersonic Viscous Flow Around a Delta Wing using Osher’s Flux Difference Splitting. In: Désidéri, JA., Glowinski, R., Périaux, J. (eds) Hypersonic Flows for Reentry Problems. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-76527-8_62

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  • DOI: https://doi.org/10.1007/978-3-642-76527-8_62

  • Publisher Name: Springer, Berlin, Heidelberg

  • Print ISBN: 978-3-642-76529-2

  • Online ISBN: 978-3-642-76527-8

  • eBook Packages: Springer Book Archive

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