Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering
Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering
Mitsubishi Heavy Industries Ltd
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
34
ページ
275 - 284
発行年
1997-01
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 6-7 JUN. 1996 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 6-7 JUN. 1996 Tokyo Japan
Numerical simulation of dynamic stall phenomena around an airfoil oscillating in a coupled mode, where the pitching and heaving oscillations have some phase differences, has been performed using the Navier-Stokes code. The propulsive efficiency and the thrust have been calculated for various combinations of the phase difference and the reduced frequency for two different feathering parameters, and the effects of the dynamic stall phenomena on the behaviors of the propulsive efficiency and thrust are also discussed in detail by examining each flow pattern obtained. The highest efficiency has been observed for the case where the pitching oscillation advances 90 deg over the heaving oscillation, for which the flow separation is confined in the small region on the airfoil surface near the trailing edge in spite of the large amplitude oscillations. For phase angles other than 90 deg the efficiency is degraded by the occurrence of the large scale leading edge separation.
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nalsp0034049.pdf
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