Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
5472961 | Aerospace Science and Technology | 2016 | 17 Pages |
Abstract
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 eN 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.
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Authors
Sergey L. Chernyshev, Marat D. Gamirullin, Vladislav Yu. Khomich, Aleksandr P. Kuryachii, Vladimir M. Litvinov, Sergei V. Manuilovich, Sergey I. Moshkunov, Igor E. Rebrov, Dmitry A. Rusyanov, Vladimir A. Yamshchikov,