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


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.


Hypersonic Flow Windward Side Delta Wing Approximate Riemann Solver Nose Region 
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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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