Effect of the Location of an Incident Shock Wave on Combustion and Flow Field of Wall Fuel-Injection
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概要
- 論文の詳細を見る
Experimental and numerical studies on the interaction between combustion of a hydrogen jet and an incident shock wave were performed. When the incident shock wave was introduced upstream of the injection slot, the boundary-layer separation region was expanded extensively. The penetration height, defined as the height of the Mach disk, with the incident shock wave was less than that without the incident shock wave. Combustion was confirmed when the incident shock wave was introduced downstream of the fuel injection slot. However, combustion was not confirmed with the incident shock wave upstream of fuel injection slot. The mechanism of these phenomena was examined based on the numerical simulation results in terms of the characteristic residence time in the separation region near the fuel injection slot.
- 社団法人 日本航空宇宙学会の論文
- 2008-11-04
著者
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NAKAMURA Hisashi
Institute of Fluid Science, Tohoku University
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KOBAYASHI Hideaki
Institute of Fluid Science, Tohoku University
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MASUYA Goro
Department of Aerospace Engineering, Tohoku University
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Masuya Goro
Dep. Of Aerospace Engineering Tohoku Univ.
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SATO Naoki
Institute of Fluid Science, Tohoku University
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Masuya Goro
Department Of Aeronautics And Space Engineering Tohoku University
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Sato Naoki
Institute Of Fluid Science Tohoku University
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Sato Naoki
Institute For Chemical Research Kyoto University
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Kobayashi Hideaki
Institute Of Fluid Science Tohoku University
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Nakamura Hisashi
Institute Of Fluid Science Tohoku University
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Nakamura Hisashi
Institute For Global Change Research Frontier Research System For Global Change:department Of Earth
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