It is critical to implement accurate and appropriate numerical methods for understanding the combustion characteristics because of the strong interactions between an inviscid core flow and multiple near-wall viscous regions. A new numerical Godunov-type scheme, which is proposed and developed for the supersonic boundary layer simulations and the hypersonic viscous flow simulations, is extended to the supersonic combustion simulations because of its simpleness, robustness and efficiency. Numerical experiments including shock-induced combustion and fuel injection non-premixed combustion are tested and the results show good performance on the comparison to experiments data, especially for the prediction of ignition position. More numerical tests should be investigated to verify and validate on complex flows for the nest.
Application of a New Shock-Stable Scheme for Supersonic Combustion Flows
2019-07-01
437593 byte
Conference paper
Electronic Resource
English
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