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Turbulent boundary layer separation control using plasma actuator at Reynolds number 2000000

Chinese Journal of Aeronautics 2016年第5期29卷 1237-1246页

作者： Zhang Xin Huang Yong Wang Xunnian Wang Wanbo Tang Kun Li Huaxing School of Aeronautics Northwestern Polytechnical University Xi'an 710072 China China Aerodynamics Research and Development Center Mianyang 621000 China

An experimental investigation was conducted to evaluate the effect of symmetrical plasma actuators on turbulent boundary layer separation control at high Reynolds number. Compared with the traditional control method of plasma actuator, the whole test model was made of aluminum and acted as a covered electrode of the symmetrical plasma actuator. The experimental study of plasma actuators＇ effect on surrounding air, a canonical zero-pressure gradient turbulent boundary, was carried out using particle image velocimetry （PIV） and laser Doppler velocimetry （LDV） in the 0.75 m × 0.75 m low speed wind tunnel to reveal the symmetrical plasma actuator characterization in an external flow. A half model of wing-body configuration was experimentally investigated in the 3.2 m low speed wind tunnel with a six-component strain gauge balance and PIV. The results show that the turbulent boundary layer separation of wing can be obviously suppressed and the maximum lift coefficient is improved at high Reynolds number with the symmetrical plasma actuator. It turns out that the maximum lift coefficient increased by approximately 8.98% and the stall angle of attack was delayed by approximately 2° at Reynolds number 2 ×10……6. The effective mechanism for the turbulent separation control by the symmetrical plasma actuators is to induce the vortex near the wing surface which could create the relatively large- scale disturbance and promote momentum mixing between low speed flow and main flow regions.

关键词： Dielectric barrier discharge Flow control Plasma actuator Turbulent boundary layer Wing-body configuration

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Experimental Investigation of the Induced Airflow of Corona Discharge

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Chinese Physics Letters 2013年第9期30卷 85-88页

作者： HUANG Yong ZHANG Xin WANG Xun-Nian WANG Wan-Bo HUANG Zong-Bo LI Hua-Xing China Aerodynamics Research and Development Center Mianyang 621000 College of Aviation Northwestern Polytechnical UniversityXi’an 710072

In order to improve the acceleration effect of corona discharge acting on air,we present an experimental study on the induced airflow produced by corona discharge between two parallel *** parameters investigated are the type of electrodes,actuation voltage and the distance in the absence of free *** induced flow velocity is measured directly in the accelerated region using the particle image velocimetry *** results show that if corona discharge is not developed into arc discharge,the induced airflow velocity increases nearly linearly with the applied voltage and the maximum induced airflow velocity near the needle electrode reaches 36m/*** is expected that in the future,the result can be referred to in the research about effect of active flow control to reach much higher induced airflow speed.

关键词： flow acceleration linearly

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Unmanned air vehicle flow separation control using dielectric barrier discharge plasma at high wind speed

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Science China(Physics,Mechanics & Astronomy) 2014年第6期57卷 1160-1168页

作者： ZHANG Xin HUANG Yong WANG WanBo WANG XunNian LI HuaXing College of Aviation Northwestern Polytechnical University China Aerodynamics Research and Development Center

The present paper described an experimental investigation of separation control of an Unmanned Aerial Vehicle(UAV)at high wind *** plasma actuator was based on Dielectric Barrier Discharge(DBD)and operated in a steady *** flow over a wing of UAV was performed with smoke flow visualization in theΦ0.75 m low speed wind tunnel to reveal the flow structure over the wing so that the locations of plasma actuators could be optimized.A full model of the UAV was experimentally investigated in theΦ3.2 m low speed wind tunnel using a six-component internal strain gauge *** effects of the key parameters,including the locations of the plasma actuators,the applied voltage amplitude and the operating frequency,were *** whole test model was made of aluminium and acted as a cathode of the *** results showed that the plasma acting on the surface of UAV could obviously suppress the boundary layer separation and reduce the model vibration at the high wind *** was found that the maximum lift coefficient of the UAV was increased by 2.5%and the lift/drag ratio was increased by about 80%at the wind speed of 100 m/*** control mechanism of the plasma actuator at the test configuration was also analyzed.

关键词： plasma actuator flow control dielectric barrier discharge unmanned air vehicle

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