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Hypersonic Delta Wing Flow Calculations using a Multidomain MUSCL Euler Solver

  • Ph. Guillen
  • M. Borrel
Conference paper

Abstract

Euler computation results for the test case 7.1.1 from a newly developed multidomain solver (FLU3M) based on an upwind/MUSCL numerical scheme are presented. The strong influence of the grid density for an accurate prediction of the flowfield specially in the vortex region is examined through three grid refinements.

Keywords

Supersonic Flow Contact Discontinuity Leeward Side Delta Wing Vortex Region 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

  1. [1]
    M. Borrel, J.L. Montagné, J. Diet, Ph. Guillen, J. Lordon: “Upwind Scheme for Supersonic Flows around Tactical Missile”; La Recherche Aérospatiale, 1988-2.Google Scholar
  2. [2]
    Ph. Guillen, M. Dormieux:Design of a 3D Multidomain Euler Code” International Seminar on Supercomputing, Boston (USA), October 3 - 5, 1989.Google Scholar
  3. [3]
    B. van Leer: “Flux Vector Splitting of the Euler Equations”; ICASE Report 82 - 30, 1982.Google Scholar
  4. [4]
    S.R. Chakravarthy: High Resolution Upwind Formulation for the Navier-Stokes Equations, VKI Lecture 1988-05.Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 1991

Authors and Affiliations

  • Ph. Guillen
    • 1
  • M. Borrel
    • 1
  1. 1.O.N.E.R.A.ChâtillonFrance

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