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 the more demanding cases. A reasonable qualitative as well as quantitative agreement was achieved.
KeywordsMach Number Pressure Contour Separation Shock Supersonic Combustion Hypersonic Flight
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