Electrogasdynamic laminar flow control on a swept wing

被引：17

作者：

Chernyshev, Sergey L. ^{[1
]}

Gamirullin, Marat D. ^{[1
]}

Khomich, Vladislav Yu. ^{[2
]}

Kuryachii, Aleksandr P. ^{[1
]}

Litvinov, Vladimir M. ^{[1
]}

Manuilovich, Sergei V. ^{[1
]}

Moshkunov, Sergey I. ^{[2
]}

Rebrov, Igor E. ^{[2
]}

Rusyanov, Dmitry A. ^{[1
]}

Yamshchikov, Vladimir A. ^{[2
]}

机构：

[1] Cent Aerohydrodynam Inst TsAGI, Zhukovsky Str 1, Zhukovskii 140180, Russia

[2] Russian Acad Sci, Inst Electrophys & Electroenerget, Dvortsovaya Nab 18, St Petersburg 191186, Russia

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2016年 / 59卷

基金：

欧洲研究理事会;

关键词：

Swept wing; Compressible boundary layer; Cross-flow-type instability; Dielectric barrier discharge actuator; DISCHARGE PLASMA ACTUATORS;

D O I：

10.1016/j.ast.2016.10.019

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The possibility of laminar flow control on a swept wing was theoretically estimated. Calculations of a 3D-compressible boundary layer on an infinite-span swept wing, including a simulatioh of the volumetric force and heat impact of dielectric barrier discharge (DBD) actuators, were. performed. The linear stability of the boundary-layer flow with respect to the stationary modes of the cross-flow-type instability was considered. The position of the laminar-to-turbulent transition was estimated using the e(N) method. Ultimate assessments of the actuator impact necessary for laminar-to-turbulent transition delay were performed for free-stream parameters corresponding to typical cruise flight conditions of subsonic civil airplanes. A simple new design for a multiple-DBD actuator intended for flow control in a thin boundary layer on a lengthy surface was proposed and studied via parametric experiments. (C) 2016 Elsevier Masson SAS. All rights reserved.

引用

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页码：155 / 161

页数：7

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