Cyber 205 dense-mesh solutions to the Euler equations for flows around the M6 and Dillner wings

  • Arthur Rizzi
Contributed Papers
Part of the Lecture Notes in Physics book series (LNP, volume 218)


The dense-mesh solutions presented here have shown that the flowfield around a trapezoidal wing like the M6 can be represented with reasonable accuracy on a standard-size mesh of say 50,000 grid points. But if the wing is one of low aspect ratio, like the Dillner delta wing, a much denser grid is required to capture the rich structure of rotating flow interacting with shock waves.


Shock Wave Euler Equation Vortex Sheet Total Pressure Loss Delta Wing 
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  1. 1.
    Fluid Dynamics Panel Working Group 07.: Test Cases for Steady Inviscid Transonic and Supersonic Flows, AGARD Pub., in preparation, 1984.Google Scholar
  2. 2.
    Rizzi, A.: Vector Coding the Finite-Volume Procedure for the CYBER 205, in Lecture Series Notes 1983-04, von Karman Institute, Brussels, 1983.Google Scholar
  3. 3.
    Vorropoulos, G. and Wendt, J.F.: Laser Velocimetry Study of Compressibility Effects on the Flow Field of a Delta Wing, AGARD-CP-342, 1983.Google Scholar
  4. 4.
    Miller, D.S. and Wood, R.M.: An Investigation of Wing Leading-Edge Vortices at Supersonic Speeds, AIAA Paper No. 83-1816, 1983.Google Scholar
  5. 5.
    Rizzi, A.W. and Eriksson, L.-E.:Computation of Flow Around Wings Based on the Euler Equations, Journal Fluid Mechanics, in press.Google Scholar

Copyright information

© Springer-Verlag 1985

Authors and Affiliations

  • Arthur Rizzi
    • 1
  1. 1.FFA The Aeronautical Research Institute of SwedenBrommaSweden

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