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

  • N. Qin
  • B. E. Richards
Conference paper

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.

Keywords

Hypersonic Flow Windward Side Delta Wing Approximate Riemann Solver Nose 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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Copyright information

© Springer-Verlag Berlin Heidelberg 1991

Authors and Affiliations

  • N. Qin
    • 1
  • B. E. Richards
    • 1
  1. 1.Department of Aerospace EngineeringUniversity of GlasgowGlasgowUK

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