Study on Advanced Aerodynamic Control Technique for Slender Body Using Multipoint Flow Control
| Project/Area Number |
24760659
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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 University of Agriculture and Technology |
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Principal Investigator |
Nishida Hiroyuki 東京農工大学, 工学(系)研究科(研究院), 准教授 (60545945)
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| Project Period (FY) |
2012-04-01 – 2016-03-31
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| Project Status |
Completed (Fiscal Year 2015)
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| Budget Amount *help |
¥4,680,000 (Direct Cost: ¥3,600,000、Indirect Cost: ¥1,080,000)
Fiscal Year 2015: ¥520,000 (Direct Cost: ¥400,000、Indirect Cost: ¥120,000)
Fiscal Year 2014: ¥650,000 (Direct Cost: ¥500,000、Indirect Cost: ¥150,000)
Fiscal Year 2013: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2012: ¥2,210,000 (Direct Cost: ¥1,700,000、Indirect Cost: ¥510,000)
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| Keywords | 流体制御 / 細長物体 / 大迎角空力 / 航空宇宙流体力学 |
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| Outline of Final Research Achievements |
When a slender body, which is typical body shape of a rocket and an air plane, flies at high angle of attack, separation flow over the body becomes asymmetric and the attitude stability is significantly lost due to the side force caused by the asymmetric separation flow. To overcome this difficulty, the plasma actuator, which is one of advanced flow control devices, was applied to the high-angle-of-attack slender body for suppressing the asymmetricity in the separation flow. As a result, this study successfully showed that the side force can be continuously changed to zero by burst-mode actuation of plasma actuators installed to the apex of the body.
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Report
(5 results)
Research Products
(33 results)
