A Study of Interaction between Shock Wave and Cross-Flow Jet Using Particle Tracking Velocimetry
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- NAKAMURA Hisashi
- 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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- OGAMI Yasuhiro
- Institute of Fluid Science, Tohoku University
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- KOBAYASHI Hideaki
- Institute of Fluid Science, Tohoku University
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抄録
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.
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52 (176), 81-88, 2009
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390001204079197440
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- NII論文ID
- 10026270278
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- NII書誌ID
- AA0086707X
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- ISSN
- 21894205
- 05493811
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- NDL書誌ID
- 10309616
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可