2010 Fiscal Year Final Research Report
Research on plasma actuator flow control that pays attention to localization flow
| Project/Area Number |
20246122
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| Research Category |
Grant-in-Aid for Scientific Research (A)
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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 | Japan Aerospace Exploration Agency |
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Principal Investigator |
FUJII Kozo Japan Aerospace Exploration Agency, 宇宙科学研究所, 教授 (50209003)
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| Co-Investigator(Kenkyū-buntansha) |
OOYAMA Akira 宇宙科学研究所, 准教授 (10373440)
FUNAKI Ikkoh 宇宙科学研究所, 准教授 (50311171)
RINOIE Kenichi 東京大学, 大学院・工学研究科, 教授 (20175037)
NONOMURA Taku 宇宙科学研究所, プロジェクト研究員 (60547967)
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| Project Period (FY) |
2008 – 2010
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| Keywords | 航空宇宙流体力学 / 流体制御 / プラズマ / 空気力学 |
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| Research Abstract |
Three-years' research for DBD plasma actuator having strong potential to improve aerodynamic performance successfully revealed detailed flow structure of the induced flow field that is associated with separation flow control. Both the experimental and numerical approach is used for better understanding of the induced flow structure. With both the approach tightly coupled, vortex flow structure induced by the DBD plasma actuator is clearly shown. The study revealed that certain types of the flow structure that promotes laminar to turbulent flow transition are the key essence of the flow separation control by the DBD plasma actuator at relatively low Reynolds numbers. The study also revealed that not the one but a few flow control mechanism may exist depending on the conditions.
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