Research has been conducted for a number of years at the NASA Langley Research Center to develop a supersonic combustion ramjet (scramjet) capable of propelling a vehicle at hypersonic speeds in the atmosphere or beyond. Recently, that research has been directed toward the optimization of the scramjet combustor, and in particular the efficiency of fuel-air mixing and reaction in the engine. This paper describes a study of fuel-air mixing and reaction in a supersonic flow field, and discusses several techniques that were applied for enhancing the mixing processes and overal combustion efficiency in the flow. Based on the results of the study, an alternate fuel injector configuration was computationally designed, and that configuration significantly increased the amount of fuel-air mixing and combustion over a given combustor length that was achieved.
Mixing and combustion enhancement in supersonic reacting flows
International Symposium on Numerical Methods in Engineering
1989-01-01
Conference paper
No indication
English
Shock-Induced Mixing Enhancement of Supersonic Turbulent Reacting Ramjet Flows
British Library Conference Proceedings | 1995
|Research on Supersonic Reacting Flows
British Library Conference Proceedings | 1994
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