Experimental cross-flow control in a 3D boundary layer by multi-discharge plasma actuators

In this work, we perform experimental studies on the electrophysical and aerodynamic characteristics of two multi-discharge actuator models using near-surface dielectric barrier discharge to generate a unidirectional volumetric force impact over an extended surface area. Flow control experiments are...

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Bibliographic Details
Published in:Aerospace science and technology 2021-05, Vol.112, p.106643, Article 106643
Main Authors: Baranov, Sergey A., Chernyshev, Sergey L., Khomich, Vladislav Yu, Kiselev, Andrey Ph, Kuryachii, Aleksandr P., Moshkunov, Sergey I., Rebrov, Igor E., Sboev, Dmitry S., Tolkachev, Stepan N., Yamshchikov, Vladimir A.
Format: Article
Language:English
Subjects:
Cross flow
Dielectric barrier discharge
Hot-wire anemometer measurements
Stationary instability vortices
Three-dimensional boundary layer
Wind tunnel experiment
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Summary:In this work, we perform experimental studies on the electrophysical and aerodynamic characteristics of two multi-discharge actuator models using near-surface dielectric barrier discharge to generate a unidirectional volumetric force impact over an extended surface area. Flow control experiments are conducted on the 3D boundary layer of a swept plate with an induced longitudinal pressure gradient using the aforementioned models in a subsonic low-turbulence wind tunnel. The results confirm the possibility of significantly decreasing the cross flow velocity in the boundary layer and stationary vortex intensity attenuation of its instability, owing to the extended volumetric force impact generated by the multi-discharge actuator system.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2021.106643