Dielectric barrier discharge plasma flat-plate turbulence flow drag reduction device

Abstract

The invention discloses a dielectric barrier discharge plasma flat-plate turbulence flow drag reduction device, which comprises upper and lower layer electrodes and an insulating dielectric layer arranged between the upper and lower layer electrodes. The upper and lower layer electrodes are connected with a high-voltage high-frequency power supply separately. The upper and lower layer electrodes are arranged in an asymmetrical manner relative to the insulating dielectric layer, and are staggered back and forth. When in use, the upper and lower layer electrodes are electrified with the high-voltage high-frequency power supply, so that air of surfaces of the drag reduction device is ionized, and charged particles move in a directed manner along an electric field under the action of an electric field force and collide with neutral air gas molecules, thereby inducing an air flow in the area to do directional movement to form a continuous jet flow. The dielectric barrier discharge plasma flat-plate turbulence flow drag reduction device has the advantages of simple working conditions, low cost, simple structure and easy mass production.

Description

technical field [0001] The invention relates to a dielectric barrier discharge plasma turbulent drag reducing device. Background technique [0002] Boundary layer control is an important research field in fluid mechanics. In turbulent boundary layers, quasi-swirl vortices are closely related to large wall frictional drag. The generation of Reynolds stress is closely related to the dynamic development of the vortex structure near the wall. The resistance change is the result of the combination of vortex structure and mass transport caused by the penetrating force acting on the fluid. Traditional boundary layer control techniques, such as the air-breathing method, require engine bleed air, which will reduce the performance of the aircraft. The wall cooling method is more difficult to achieve in flight and is not suitable for actual aircraft engineering applications. Therefore, novel plasma active flow control techniques applied to the boundary layer have been developed. ...

AI Technical Summary

Problems solved by technology

Traditional boundary layer control techniques, such as the air-blowing method, require engine bleed air, which will reduce the performance of the aircraft. The wall cooling method is more difficult to achieve in flight and is not suitable for actual aircraft engineering applications

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