Hypersonic Delta Wing Flow Calculations using a Multidomain MUSCL Euler Solver
Euler computation results for the test case 7.1.1 from a newly developed multidomain solver (FLU3M) based on an upwind/MUSCL numerical scheme are presented. The strong influence of the grid density for an accurate prediction of the flowfield specially in the vortex region is examined through three grid refinements.
KeywordsSupersonic Flow Contact Discontinuity Leeward Side Delta Wing Vortex Region
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