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Plasma-based aircraft aerodynamic characteristic analysis method

A technology of plasma and analysis method, which is applied in the field of analysis of the aerodynamic characteristics of aircraft by plasma exciters, and can solve problems such as increasing the stealth performance of aircraft, low efficiency, and potential safety hazards of aircraft

Active Publication Date: 2017-10-10
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

Under conventional aerodynamic conditions, the efficiency of controlling the rudder surface is low when flying at high angles of attack, or even completely loses efficiency, which brings safety hazards to the aircraft flying at high angles of attack; In addition to flight efficiency at high angle of attack, it can also greatly increase the stealth performance of the aircraft

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Embodiment Construction

[0059] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0060] In order to change the aerodynamic characteristics of the traditional aircraft with low lift coefficient and high drag coefficient, the present invention proposes an analysis method for the aerodynamic characteristics of the aircraft based on a plasma actuator. The method is to install a dielectric barrier discharge (DBD) exciter on the wing of the aircraft when the Mach number is 5, and a high-voltage high-frequency power supply is passed between the exposed electrode and the covered electrode of the DBD exciter. The gas will be broken down to generate discharge, and the DBD exciter will generate wall jets in the direction of the electric field, and at the same time generate jets perpendicular to the wall, accompanied by the shock wave injection effect and local temperature field changes, so as to realize the control of the flow field on the wing surface ...

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Abstract

The invention relates to a plasma-based aircraft aerodynamic characteristic analysis method. According to the method, the lift coefficient is improved and the drag coefficient is reduced based on the dielectric barrier discharge (DBD) plasma control technology. The lift-drag ratio of an aircraft is improved and the aerodynamic characteristic performance of the aircraft is improved. Furthermore, in the dielectric barrier discharge (DBD) plasma condition, the aerodynamic characteristics of the surface of the aircraft can be analyzed and obtained.

Description

technical field [0001] The invention relates to the technical field of aircraft aerodynamic characteristics, in particular to a method for analyzing the aerodynamic characteristics of aircraft by a dielectric barrier discharge plasma actuator. Background technique [0002] Today's aircraft pose higher challenges to aerodynamic performance, and traditional aerodynamic design methods are based on non-plasmaized air media. Under conventional aerodynamic conditions, the efficiency of controlling the rudder surface is low when flying at high angles of attack, or even completely loses efficiency, which brings safety hazards to the aircraft flying at high angles of attack; In addition to the flight efficiency of the high angle of attack, it can also greatly increase the stealth performance of the aircraft. Plasma flow control technology can increase the lift of the aircraft, reduce the drag, and increase the lift-to-drag ratio, thereby improving the aerodynamic performance of the ...

Claims

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Application Information

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IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 王鑫张鹏飞石磊张叶荣
Owner NORTHWESTERN POLYTECHNICAL UNIV
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