Electrogasdynamic laminar flow control on a swept wing

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• 作者：Sergey L. Chernyshev^a ; Marat D. Gamirullin^a ; Vladislav Yu. Khomich^b ; Aleksandr P. Kuryachii^a ; ^{kuryachiy@yahoo.com" class="auth_mail" title="E-mail the corresponding author} ; Vladimir M. Litvinov^a ; Sergei V. Manuilovich^a ; Sergey I. Moshkunov^b ; Igor E. Rebrov^b ; Dmitry A. Rusyanov^a ; Vladimir A. Yamshchikov^b
• 关键词：Swept wing ; Compressible boundary layer ; Cross-flow-type instability ; Dielectric barrier discharge actuator
• 刊名：Aerospace Science and Technology
• 出版年：2016
• 出版时间：December 2016
• 年：2016
• 卷：59
• 期：Complete
• 页码：155-161
• 全文大小：1000 K

文摘

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 simulation 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.