@article{oai:jaxa.repo.nii.ac.jp:00022623,
 author = {郭, 東潤 and 雷, 忠 and 野口, 正芳 and Kwak, Dongyoun and Lei, Zhong and Noguchi, Masayoshi},
 issue = {3},
 journal = {日本航空宇宙学会論文集, Journal of the Japan Society for Aeronautical and Space Sciences},
 month = {Jun},
 note = {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, 資料番号: PA1520038000},
 pages = {83(7)--88(12)},
 title = {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},
 volume = {63},
 year = {2015}
}