Numerical Methods for Simulating Supersonic Combustion
An efficient computer program was developed for the computation of supersonic combustion problems. Several test cases showed the capabilities of implementations of different upwind schemes in calculating chemical reactions. The FAS multigrid procedure accelerated in some cases the convergence to steady state. The numerical results were validated by the corresponding experiments for one of the more demanding cases. A reasonable qualitative as well as quantitative agreement was achieved. A relatively high degree of numerical efficiency was achieved by parallel implementation of the code, using domain decomposition.
KeywordsMach Number Hypersonic Flow Processor Unit Separation Shock Hypersonic Flight
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