学術雑誌論文 デルタ形状ボルテックスジェネレーターによる後縁フラップ上の剥離流れ制御について
Control of Flow Separation on Trailing Edge Flap Using a Delta-Shaped Vortex Generators

郭, 東潤  ,  雷, 忠  ,  野口, 正芳  ,  Kwak, Dongyoun  ,  Lei, Zhong  ,  Noguchi, Masayoshi

63 ( 3 )  , pp.83(7) - 88(12) , 2015-06-05 , 日本航空宇宙学会 , The Japan Society for Aeronautical and Space Sciences
ISSN:1344-6460
NII書誌ID(NCID):AA11307372
内容記述
Low-speed wind tunnel tests were performed to investigate aerodynamic effects induced by delta-shaped vortex generators installed on the upper surface of a trailing-edge flap. The vortex generator was applied to control the flow field around the trailing-edge flap where the flow was separated from the hinge line of the trailing-edge flap. The test results showed that the vortex generators increase the lift coefficient and the lift-to-drag ratio when the trailing-edge flap deflects to 30 degrees. The leading-edge separation vortices formed from the delta-shaped vortex generators suppressed the flow separation on the trailing-edge flap. The height of the vortex generator geometrically changes depending on the trailing-edge flap deflection angles. Therefore, when the trailing-edge flap is not deflected such as cruise flight condition where the flow field is dominated by the attached flow, the vortex generator does not impose a penalty on the aerodynamic performance.
形態: 図版あり
Physical characteristics: Original contains illustrations

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