Effect of gurney flaps on a nonslender delta wing during large-amplitude and high-frequency dynamic pitching

被引：3

作者：

Tang, Wenxuan ^{[1
]}

Liu, Peiqing ^{[1
]}

Hu, Tianxiang ^{[1
]}

Qu, Qiulin ^{[1
]}

Guo, Hao ^{[1
]}

Liu, Yuan ^{[1
]}

Akkermans, Rinie A. D. ^{[2
]}

机构：

[1] Beihang Univ, Lu Shijia Lab, Beijing 100191, Peoples R China

[2] Hamburg Univ Appl Sci, Dept Automot & Aeronaut Engn, Hamburg, Germany

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2023年 / 143卷

基金：

中国国家自然科学基金;

关键词：

Nonslender delta wing; Pitching oscillation; High frequency; Gurney flap; LEADING-EDGE VORTICES; VORTEX BREAKDOWN; LIFT ENHANCEMENT; FLOW-CONTROL; UNSTEADY AERODYNAMICS; CANARD-CONFIGURATION; SLENDER; MECHANISMS; AIRCRAFT; TUNNEL;

D O I：

10.1016/j.ast.2023.108715

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The flow control effect of Gurney flaps on 50 degrees swept delta wings during large-amplitude and high-frequency pitching were investigated both experimentally and numerically. Both force and velocity measurements were conducted and compared with the numerical simulation results. The lift hysteresis was found to be significantly affected by the Gurney flaps. It was found that the leading-edge Gurney flap (LG) acts to redistribute the vorticity over the suction surface of the wing during the upstroke process. The formation and development of the leadingedge vortex (LEV) on the suction surface was delayed by the LG, which was accompanied by enhancement of the lift at high angles of attack. The lower surface pressure can be altered with the flow velocity being slowed down by the trailing-edge Gurney flap (TG), which improves overall lift performance of the pitching wing at small to moderate angles of attack.

引用

页数：17

共 28 条

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