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ID 56125
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Author
Kouchi, Toshinori graduate school of Natural Science and Technology, Okayama University
Masuya, Goro Tohoku University
Mitani, Tohru Japan Aerospace Exploration Agency
Tomioka, Sadatake Japan Aerospace Exploration Agency
Abstract
A sidewall compression scramjet engine operated in two combustion modes under Mach 6 flight condition, weak- and intensive-combustion modes. The weak mode occurred below the overall fuel equivalence ratio (Φ) of around 0.4. Transition from the weak mode to the intensive mode occurred at Φ ~ 0.4, accompanied by a sudden increase in thrust. Mechanisms of the transition were numerically investigated in this study. Our simulations captured the sudden increase in thrust at the mode transition. In the weak mode, combustion occurred in only a region near the topwall where an igniter was installed. The combustion region expanded toward the cowl with boundary-layer separation at the mode transition. Our simulations demonstrated that low ignition capability resulted in the weak mode. We demonstrated that the presence of additional igniters on the sidewalls improved the ignition capability and achieved the intensive mode in the entire Φ range.
Note
This is an Accepted Manuscript of an article published by American Institute of Aeronautics and Astronautics
Published Date
2012
Publication Title
Journal of Propulsion and Power
Volume
volume28
Issue
issue1
Publisher
American Institute of Aeronautics and Astronautics
Start Page
106
End Page
112
ISSN
07484658
NCID
AA10459896
Content Type
Journal Article
language
英語
OAI-PMH Set
岡山大学
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DOI
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Related Url
isVersionOf https://doi.org/10.2514/1.B34172