| Project/Area Number |
25420139
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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| Section | 一般 |
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| Research Field |
Fluid engineering
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
IKEDA Tomoaki 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 研究員 (00443276)
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| Co-Investigator(Kenkyū-buntansha) |
ATOBE Takashi 国立研究開発法人 宇宙航空研究開発機構, 航空技術部門, 主幹研究員 (80358663)
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| Co-Investigator(Renkei-kenkyūsha) |
ASAI Keisuke 東北大学, 大学院工学研究科, 教授 (40358669)
NAGAI Hiroki 東北大学, 大学院工学研究科, 准教授 (70360724)
KONISHI Yasufumi 東北大学, 流体科学研究所, 特任准教授 (20552540)
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| Project Period (FY) |
2013-04-01 – 2016-03-31
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| Project Status |
Completed (Fiscal Year 2015)
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| Budget Amount *help |
¥4,940,000 (Direct Cost: ¥3,800,000、Indirect Cost: ¥1,140,000)
Fiscal Year 2015: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2014: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
Fiscal Year 2013: ¥1,820,000 (Direct Cost: ¥1,400,000、Indirect Cost: ¥420,000)
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| Keywords | 翼設計 / 非定常空力 / 空力音響 / 低レイノルズ数 / 境界層 |
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| Outline of Final Research Achievements |
We conducted airfoil design optimization studies for low Reynolds number, rarefied atmospheric environment, such as ultra high altitude, or Mars atmospheric flight, for three years. In low Reynolds number flight, the unsteady vortical motion in relatively large scale becomes more dominant. We performed both numerical simulations and wind tunnel tests for various airfoil shapes to clarify the onset mechanism of unsteady motions. For a better aerodynamic performance, the airfoil shape near the leading edge should stay flat, while the maximum camber location should be given near the trailing edge, for very thin thickness. Our achievements were reported in academic journals and conferences.
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