Method of controlling plasma circular rector for wing with sharp trailing edge

Abstract

The invention provides a method of controlling a plasma circular rector for a wing with a sharp trailing edge, and is characterized in that one or more of plasma exciters are attached on a place on a wing suction surface, which is close to a trailing edge, a covering electrode is close to the trailing edge, one or more of another plasma exciters are attached on a place on a wing pressure surface, which is close to the trailing edge, and a bare electrode is close to the trailing edge. According to the invention, the wall surface jet flow toward a downstream trailing edge direction is generated by the plasma exciters attached on the suction surface under the drive of field stress, and the wall surface jet flow toward an upstream trailing edge direction is generated by the plasma exciters attached on the pressure surface under the drive of field stress. In comparison with a blow type circular rector control, the method, provided by the invention, has wider application range, and is suitable for the wing with the sharp trailing edge; and the adopted structure is simple and is easy to install and implement without an additional air source, and meanwhile, the active control of wing lift is realized, and the method has huge advantages and development potential.

Description

technical field [0001] The invention relates to a plasma circulation control technology suitable for sharp trailing edge wings, specifically through the special arrangement of two or more plasma actuators at the trailing edge of the wing tip to modify the flow around the wing , for the purpose of circulation control. Background technique [0002] In the field of aerospace engineering, increasing lift and reducing drag has always been the focus of researchers. Circulation control is a control method developed based on the basic phenomenon of fluid mechanics - "Konda effect", which can effectively increase the lift of the aircraft. The specific implementation scheme of circulation control in practical application is as follows: figure 1 As shown, there is a slot on the upper part of the Coanda curved surface trailing edge 1b of the wing, and high-pressure gas is ejected from the slot 2, which accelerates the boundary layer flow velocity near the curved wall trailing edge. A...

AI Technical Summary

Problems solved by technology

At this time, due to the use of the blunt trailing edge of the wing, it will bring a large increase in additional resistance, which seriously affects the economical efficiency of the aircraft.

[0003] In addition, another defect of the traditional circulation control method is that certain moving parts and an air source with sufficient power are required to generate jet flow, which will lead to a decrease in engine efficiency, and at the same time increase the complexity and structural weight of the wing, causing difficulties in wing design

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