Inviscid Calculations by an Upwind Finite Element Method of Hypersonic Flows over a Double (Single) Ellipse
The quest for better designed reentry vehicles has caused the development of more sophisticated solution algorithms which take into account the complex chemical phenomena associated with high speed flows. As a result, the number of variables involved and the complexity of the equations has increased considerably. In this context, the optimization of the number of mesh points required for a given solution accuracy is of paramount importance. We feel that unstructured grids are best suited to handle large variation of grid size, placing more points exactly where needed and allowing a straightforward implementation of adaptive strategies. We have therefore chosen in this work an unstructered grid approach and developed an inviscid flow solver able to operate on such grids. This solver employes an hybrid finite volume/finite element algorithm and some upwind concepts reformulated in the context of unstructured triangular grids. The upwind decomposition of the fluxes provides a way to obtain accurate and robust schemes, able to cope effectively with very strong shock phenomena.
KeywordsMach Number Unstructured Grid Hypersonic Flow Inviscid Flow Equilibrium Flow
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