A Study of Interaction between Shock Wave and Cross-Flow Jet Using Particle Tracking Velocimetry
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概要
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An experimental study was performed to investigate the flame-holding of a hydrogen jet injected into a supersonic cross-flow interacting with an incident shock wave. Pre-burned rich hydrogen or air was injected into the supersonic airflow at Mach 2.5. The injection pressure was 1.2 MPa or 1.6 MPa. The deflection angle of the shock generator was 10°. Velocity profiles near the wall and of the recirculation zone around the injection slot could successfully be measured using the PTV method newly-devised in this study. The velocity profiles showed that the reattachment point of the recirculation zone downstream of the injection slot moved further downstream when the incident shock wave was introduced downstream of the injection slot. The reattachment point with the incident shock wave at the injection pressure of 1.6 MPa was not very different from that of 1.2 MPa. However, the extinction limit at the injection pressure of 1.6 MPa extended further than that of 1.2 MPa.
- 社団法人 日本航空宇宙学会の論文
- 2009-08-04
著者
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OGAMI Yasuhiro
Institute of Fluid Science, Tohoku University
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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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Ogami Yasuhiro
Institute Of Fluid Science Tohoku University
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SATO Naoki
Institute of Fluid Science, Tohoku University
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ISHIDA Syunsuke
Institute of Fluid Science, 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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Ishida Syunsuke
Institute Of Fluid Science Tohoku 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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