Numerical study of mixing and combustion process of a scramjet engine model
説明
In this study, a numerical analysis of combusting flows was made on the scramjet engine which has been tested at the Ramjet engine Test Facility (RJTF) of the Kakuda Research Center. Our main purpose is to numerically investigate the change of engine performance at Mach 8 flight condition such as mixing and combustion within the combustor and resulting engine thrust with increasing the fuel equivalence ratio as well as the transition mechanism from start to unstart condition. CFD results showed good agreement with experiments qualitatively and quantitatively. We made some considerations on the features of the fuel/air mixing and combustion process in the engine.
収録刊行物
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- 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference
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10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001-04-24
American Institute of Aeronautics and Astronautics (AIAA)