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2015 Fiscal Year Final Research Report

Airfoil optimization study in unsteady low Reynolds number flow

Research Project

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Project/Area Number 25420139
Research Category

Grant-in-Aid for Scientific Research (C)

Allocation TypeMulti-year Fund
Section一般
Research Field Fluid engineering
Research InstitutionJapan Aerospace EXploration Agency

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)

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)
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)
Project Period (FY) 2013-04-01 – 2016-03-31
Keywords翼設計 / 非定常空力 / 空力音響
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.

Free Research Field

数値流体力学

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Published: 2017-05-10  

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