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Artificial turbulization of the supersonic boundary layer by dielectric barrier discharge

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The most evident way to decrease drag and pollution of transonic airplanes is extensive using of laminar flow wherever it is possible. Unfortunately the laminar flows are difficult to implement in presence of adverse pressure gradients caused by the shock wave / boundary layer interaction. Undesirable flow separation may eliminate all advantages of the laminar flow. Therefore it is necessary to design a technique of fast and reliable turbulization of the boundary layer right upstream of the interaction zone to reduce the separation. The paper is devoted to experimental and numerical study of plasma application for turbulization of the boundary layers at M=1.52. The experiments demonstrated the possibility of the supersonic boundary layer turbulization by the dielectric barrier discharge. Parametric study of this effect was performed by CFD to find the mechanisms of the turbulization and optimize plasma discharge parameters.

Author(s):

Pavel Polivanov    
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Russian Federation

Andrey Sidorenko    
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Russian Federation

Anatoly Maslov    
Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Russian Federation