Rotating Detonation in High-speed Combustible Flows Using A ShockTunnel
| Project/Area Number |
23656536
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| Research Category |
Grant-in-Aid for Challenging Exploratory Research
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Yokohama National University |
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Principal Investigator |
ISHII Kazuhiro 横浜国立大学, 大学院・工学研究院, 教授 (20251754)
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| Project Period (FY) |
2011 – 2012
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| Project Status |
Completed (Fiscal Year 2012)
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| Budget Amount *help |
¥4,030,000 (Direct Cost: ¥3,100,000、Indirect Cost: ¥930,000)
Fiscal Year 2012: ¥910,000 (Direct Cost: ¥700,000、Indirect Cost: ¥210,000)
Fiscal Year 2011: ¥3,120,000 (Direct Cost: ¥2,400,000、Indirect Cost: ¥720,000)
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| Keywords | デトネーション / 推進機関 / 衝撃波 / 推進 / エンジン |
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| Research Abstract |
An experimental study has been made on initiation and propagation of rotating detonation waves. A test gas behind a reflected shock wave in a shock tunnel flows into an annular combustion chamber through an orifice plate to clarify conditions of steady propagation of rotating detonation waves. By varying the pressure ratio across the orifice plate, it is found that rotating detonation is achieved for the pressure ratio of 7.5, whereas the pressure ratio of 2.5 results in flash-back. The present study clarifies the pressure ratio needed for stable condition for initiation of rotating detonation waves.
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Report
(3 results)
Research Products
(4 results)
