2000 Fiscal Year Final Research Report Summary
Transition Measurement and Prediction of a Supersonic Experimental Aircraft Wing Boundary Layer
| Project/Area Number |
10555333
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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 | 展開研究 |
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| Research Field |
Aerospace engineering
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| Research Institution | TOHOKU UNIVERSITY |
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Principal Investigator |
KOHAMA Yasuaki Tohoku University, Institute of Fluid Science, Professor, 流体科学研究所, 教授 (60006202)
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| Co-Investigator(Kenkyū-buntansha) |
FUKUNISHI Yu School of Engineering, Tohoku University, Professor, 大学院・工学研究科, 教授 (60189967)
IKOHAGI Toshiaki Institute of Fluid Science, Tohoku University, Professor, 流体科学研究所, 教授 (90091652)
NAKAHASHI Kazuhiro School of Engineering, Tohoku University, Professor, 大学院・工学研究科, 教授 (00207854)
WATANABE Hideo Institute of Fluid Science, Tohoku University, Research Associate, 流体科学研究所, 助手 (10006190)
OHBAYASHI Shigeru Institute of Fluid Science, Tohoku University, Associate Professors, 流体科学研究所, 助教授 (80183028)
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| Project Period (FY) |
1998 – 2000
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| Keywords | Next generation aircraft / Drag-reduction method / Flight test / Transitionmeasurement / Boundary layer control |
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| Research Abstract |
Through 3 years of the this research project, we have succeeded to clarify the complicated 3D transition mechanism. Especially, swept wing boundary layer transition mechanism is as follows.
Stream wise stationary vortex system start to appear as the primary instability. Unsteady wave instabilities of two different frequency modes are induced by this stationary vortices. High frequency secondary instability is considered to be the key sequence for the turbulent transition. By sucking the low momentum flow selectively at the position of stationary vortices, we have succeeded to delay the transition with at least 1/3 of the suction volume compared with the uniform suction case.
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Research Products
(16 results)
