21st Congress of International Council of the Aeronautical Sciences, Melbourne, Australia, 13-18 September, 1998
Paper ICAS-98-2.2.3

ADAPTIVE MESH REFINEMENT ON THE SOLUTION OF TWO-DIMENSIONAL VISCOUS AEROSPACE PROBLEMS

Korzenowski H., Maciel E. S. G., Azevedo J. L. F.
CTA/ITA/IEAA, Brazil; *CTA/IAE/ ASE-N, Brazil

Keywords: adaptive mesh refinement, two-dimensional viscous aerospace

A study of adaptive mesh refinement and of high resolution flux-vector splitting schemes on the solution of 2-D aerospace problems is described. The emphasis of the work is in developing the capability of accurately simulating realistic viscous flows of aerospace interest. The governing equations are discretized in a cell centered, finite volume procedure for unstructured triangular grids. Spatial discretization considers three different schemes, including a centered and two upwind schemes. Time march uses an explicit, 2nd-order accurate, 5-stage Runge-Kutta time stepping scheme. Results are presented for adaptive inviscid simulations of the flow in a hypersonic inlet configuration. Viscous simulations have considered airfoil flows, transonic convergent-divergent nozzle cases and the hypersonic inlet configuration. For all cases considered, the results have shown good qualitative agreement with the expected flow features.

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