Boundary-Layer Transition Control by Plasma Crossflow Reduction in Swept Wing

被引：0

作者：

Miwa, Yuto ^{[1
]}

Yoshimi, Ikuya ^{[1
]}

Matsuno, Takashi ^{[1
]}

Kwak, Dongyoun ^{[2
]}

机构：

[1] Tottori Univ, Tottori 6808552, Japan

[2] Japan Aerosp Explorat Agcy, Mitaka, Tokyo 1810015, Japan

来源：

PROCEEDINGS OF THE 2021 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY (APISAT 2021), VOL 1 | 2023年 / 912卷

关键词：

Boundary layer; Transition; Flow control; Plasma actuator;

D O I：

10.1007/978-981-19-2689-1_56

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The boundary-layer transition caused by the crossflow instability in a swept wing is controlled by a plasma actuator (PA). In this study, the control concept is to suppress the crossflow generated at leading edge of the wing by using PAs. The PAs are installed at the leading edge so that the body force can be applied in the direction that cancels the crossflow. An attempt was made to delay the boundary-layer transition by driving a PA. In a wind tunnel experiment, we investigate the transition position and velocity in the boundary layer at U = 20 m/s. The experimental results showed that the transition position delayed when PA was driven. From the spectral analysis of the velocity in the boundary layer, we found that the boundary-layer transition process changed from crossflow instability mode when PA was driven.

引用

页码：719 / 731

页数：13

共 13 条

[1]

AokiK MutoK, 2010, T JSME B, V76, P1473

[2]

Carpenter Andrew, 2008, 26 AIAA APPL AER C, P7335

[3] Laminar flow control research at TsAGI: Past and present [J].