| Project/Area Number |
24560210
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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| Section | 一般 |
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| Research Field |
Fluid engineering
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| Research Institution | Tokyo University of Science |
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Principal Investigator |
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| Co-Investigator(Kenkyū-buntansha) |
HONAMI Shinji 東京理科大学, 工学部, 教授 (30089312)
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| Co-Investigator(Renkei-kenkyūsha) |
SETO Takafumi 金沢大学, 自然システム学系, 教授 (40344155)
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| Project Period (FY) |
2012-04-01 – 2015-03-31
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| Project Status |
Completed (Fiscal Year 2014)
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| Budget Amount *help |
¥4,420,000 (Direct Cost: ¥3,400,000、Indirect Cost: ¥1,020,000)
Fiscal Year 2014: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2013: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2012: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
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| Keywords | 流体制御 / アクチュエータ / プラズマ / はく離 / 翼 |
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| Outline of Final Research Achievements |
The purpose of this study is to develop a micro plasma actuator as a new saving energy device for flow separation control. The size of the micro plasma actuator in which electrode is the order of under millimeter size is smaller than that of conventional type plasma actuator. First, the characteristics of the a micro plasma actuator was researched by flow visualization. The jet velocity was about 0.3 m/s in quiescent air. Wind tunnel measurement was performed to investigate the wake structure behind flat plate wing with straight type macro plasma actuator. Then we developed sine curved type micro plasma actuator which is possible to induce streamwise vortex by jet collision. The sine curve type macro plasma actuator was installed on the surface of NACA 0012 wing. It was confirmed that the energy consumption of the micro plasma actuator was lower than that of normal plasma actuator by using V-Q Lissajous method.
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