Computation of three-dimensional vortex flows past wings using the EULER Equations and a multiple-grid scheme
A numerical method for solving the EULER Equations is presented, which is well suited to the computation or flows containing strong shock waves, and complex vortex structures. The EULER equations system is written in a pseudo-unsteady form, with constant total enthalpy ; it is integrated step by step in time with the explicit finite-volume scheme of Ron-Ho NI. Convergence speeding-up is achieved using NI's multiple-grid procedure. The farfield boundary conditions are treated with the compatibility relations technique. The computed examples presented concern the ONERA-M6 wing, and a sharp leading-edged delta wing, the DILLNER wing.
KeywordsEULER Equation Vortex Sheet Strong Shock Wave Farfield Boundary Condition Complex Vortex Structure
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- 1.Ron-Ho NI “A multiple-grid scheme for solving the EULER Equations” AIAA Journal, november 1982.Google Scholar
- 2.N. Viviand “Pseudo-unsteady methods for transonic flow computation” Lecture note in physics, vol. 141 Springer Verlag, Berlin (1980).Google Scholar
- 3.A. JAMESON “Numerical solution of the EULER Equations for compressible inviscid fluids” 6 th ICCMAS Versailles, FRANCE december 1983.Google Scholar
- 4.C. KOECK and M. NERON “Computation of 3D inviscid flow on a wing by pseudo-unsteady resolution of the CULER Equations” 5 th GAMM conference ROMA October 1983 Viewer Verlag.Google Scholar
- 5.M. Bredif “A multigrid finite-element method for transonic potential flow” AIAA paper 83-0507.Google Scholar