Suppression control of tonal trailing-edge noise using a plasma actuator
| Project/Area Number |
24760664
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Tokyo Metropolitan University |
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Principal Investigator |
INASAWA Ayumu 首都大学東京, システムデザイン研究科, 准教授 (70404936)
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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 |
¥4,550,000 (Direct Cost: ¥3,500,000、Indirect Cost: ¥1,050,000)
Fiscal Year 2014: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2013: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2012: ¥2,210,000 (Direct Cost: ¥1,700,000、Indirect Cost: ¥510,000)
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| Keywords | 空力音 / プラズマアクチュエータ / 境界層 / 不安定性 / トレーリングエッジノイズ / 受容性 / 流れの不安定性 |
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| Outline of Final Research Achievements |
Suppression control of tonal noise radiation from an airfoil trailing edge is conducted by using a plasma actuator for a NACA0012 airfoil at a chord Reynolds number Re = 220,000. To minimize possible interferences of two-dimensional electrode to the boundary-layer stability, a specially-designed actuator with flush-mounted configuration is employed. It is found that the weak wall jet induced by the two-dimensional actuator can reduce the boundary-layer instability significantly, leading to the efficient suppression control of trailing-edge noise. Suppression of tonal noise is also achieved by weakening two-dimensionality of developing instability waves at the airfoil trailing-edge.
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Report
(4 results)
Research Products
(5 results)
