| Project/Area Number |
23360377
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Okayama University (2012-2013)
Tohoku University (2011) |
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Principal Investigator |
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| Co-Investigator(Kenkyū-buntansha) |
MASUYA Goro 東北大学, 大学院・工学研究科, 教授 (20271869)
TAKITA Kenichi 東北大学, 大学院・工学研究科, 准教授 (80282101)
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| Co-Investigator(Renkei-kenkyūsha) |
TOMIOKA Sadatake 独立行政法人宇宙航空研究開発機構, 角田宇宙センター, 領域サブリーダ (50358553)
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| Project Period (FY) |
2011-04-01 – 2014-03-31
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| Project Status |
Completed (Fiscal Year 2013)
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| Budget Amount *help |
¥19,110,000 (Direct Cost: ¥14,700,000、Indirect Cost: ¥4,410,000)
Fiscal Year 2013: ¥1,820,000 (Direct Cost: ¥1,400,000、Indirect Cost: ¥420,000)
Fiscal Year 2012: ¥2,600,000 (Direct Cost: ¥2,000,000、Indirect Cost: ¥600,000)
Fiscal Year 2011: ¥14,690,000 (Direct Cost: ¥11,300,000、Indirect Cost: ¥3,390,000)
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| Keywords | 推進工学 / 航空宇宙工学 / 混合促進 / 超音速燃焼 / スクラムジェットエンジン / レーザ計測 |
|---|
| Research Abstract |
Scramjet engine is one of the promising candidates as a propulsion system for hypersonic flight vehicles and space planes. We developed a combined stereoscopic Particle Image Velocimetry (PIV) and acetone Planar Laser Induced Fluoresce (PLIF) measurement system, to evaluate turbulent eddy diffusion flux in the combustor, which physically means the averaged transport due to turbulent fluctuations. We applied this measurement system to a transverse jet in a Mach 2 supersonic flow with/without pseudo shock wave, simulating the scramjet combustor. The system successfully measured the eddy flux in the flowfield. These quantitative data provided insight into the fundamental physics of the supersonic mixing.
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