Volume 36, Number 5, October 2018
|Page(s)||963 - 969|
|Published online||17 December 2018|
Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft
Beijing Electro-Mechanical Engineering Institute, Beijing
2 College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
The nanosecond pulsed plasma discharge actuator is used on a flying wing aircraft. At the angles of attack rang from -4° to 28°, the impact of plasma actuator arrangement position and discharge frequency on lift-enhancement effect is tested. Oil flow visualization is used to investigate the surface flow pattern varies with angles of attack for the plasma actuator turned on and off. The result indicates that lift-enhancement can be achieved through the actuator discharges at large angles of attack on flying wing aircraft. The arrangement position and discharge frequency both have a significant impact on lift-enhancement effect. The actuator which arranged at the leading edge of the aircraft could get the best lift-enhancement effect. There exists an optimal discharge frequency, flow separation under this frequency can be effectively suppressed, which results the best lift-enhancement effect. The flow visualization test shows that the control mechanisms of the plasma actuator are to inject energy to the shear layer, thus increased the vortex strength. The vortices strengthen the mixing of the outer high-speed fluid with inner low-speed fluid, which effectively restrains the separation.
Key words: plasma actuator / flying wing / lift-enhancement / oil flow / angle of attack / flow separation / flow visualization / wind tunnel experiment
关键字 : 等离子体 / 飞翼布局 / 增升 / 油流 / 攻角 / 流动分离 / 流动显示 / 风洞试验
© 2018 Journal of Northwestern Polytechnical University. All rights reserved.
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