| Project/Area Number |
22760626
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Waseda University |
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Principal Investigator |
TEZUKA Asei 早稲田大学, 理工学術院, 准教授 (50361506)
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| Project Period (FY) |
2010 – 2011
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| Project Status |
Completed (Fiscal Year 2011)
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| Budget Amount *help |
¥4,160,000 (Direct Cost: ¥3,200,000、Indirect Cost: ¥960,000)
Fiscal Year 2011: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2010: ¥3,120,000 (Direct Cost: ¥2,400,000、Indirect Cost: ¥720,000)
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| Keywords | 航空宇宙流体力学 / 超小型飛行機 / プラズマアクチュエータ / 低レイノルズ数流れ / バースト周波数 / 翼型 / 層流剥離 / 流れの安定性 / 空気力学 / 航空宇宙流体 / 非圧縮流 / 数値流体力学 |
|---|
| Research Abstract |
The lift coefficient of thick airfoil becomes essentially zero at low Reynolds number and low attack angle, for the laminar separated flow does not reattach at the trailing edge. According to the increase in the attack angle, the laminar separated region becomes unstable and the flow becomes oscillatory, which lead to the flow reattachment and the steep increase in the lift coefficient. This research demonstrated that, by installing a plasma actuator near the trailing edge of the airfoil and artificially inducing steady flow or oscillatory flow, we can increase the lift coefficient.
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