Experimental study on drag reduction of L-shaped bluff body by AC-DBD plasma actuation
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摘要: 等离子体流动控制是一种应用广泛的主动流动控制技术。为进一步研究其机理、拓展其应用范围，针对L形截面钝体模型，采用3种AC-DBD（介质阻挡放电）等离子体激励器布置形式，比较了施加激励后的减阻效果，并对减阻机理进行了研究。实验在南京航空航天大学0.8 m低速直流风洞中进行（风向角0°、来流速度2~8 m/s），激励器布置形式为顺来流前缘激励、逆来流前缘激励和拐角激励。研究结果表明：不同来流速度下，等离子体激励器对L形截面钝体都有一定的减阻效果，且减阻效果随流速增大而降低；拐角激励减阻效果最佳，逆来流前缘激励次之，顺来流前缘激励最差；通过流场分析，说明了激励器布置形式变化产生了不同的扰动效果；不同的流动控制机理是影响减阻效果的关键因素。Abstract: Plasma flow control is a widely used active flow control method. In order to further expand the application scope and understand the actuation mechanism, three kinds of AC-DBD (Dielectric Barrier Discharge) plasma actuator layout forms are used to compare the drag reduction capabilities of the L-shaped model after actuation, and the drag reduction mechanism is studied. The experiment is carried out in a low-speed DC wind tunnel, with a wind direction angle of 0°, and a wind speed of 2-8 m/s. These different actuators layout forms are the plasma actuator placed close to the leading edge along the incoming flow direction, the plasma actuator placed close to the leading edge against the incoming flow direction, and the plasma actuator arranged at the corner, respectively. Research shows that plasma actuators under different wind speed conditions have a certain control effect on drag reduction of bluff bodies, and the control ability decreases with the increase of wind speed. The plasma actuator placed in the corner produces the best control effect, and the drag reduction rate can reach more than 13% at low speed. The plasma actuator placed close to the leading edge against the incoming flow direction produces a similar effect. The drag reduction rate of the plasma actuator near the leading edge along the inflow direction can only reach about 7% at most. By analyzing the flow field, it is shown that the change of layout position produces different disturbance effects. Different flow control mechan-isms are the key factors affecting the actuation effect.
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图 1 模型受风面编号、风向角定义及测压点
Figure 1. The number of each surface of the model and the definition of wind direction angle
图 5 不同布置形式的激励器施加激励后的整体减阻率
Figure 5. Drag reduction rate after actuation of different layout actuators
图 6 不同布置形式的激励器施加激励后各测压点的风压折减系数
Figure 6. The pressure reduction coefficient of each pressure tap after actuation
图 7 施加激励前后不同流速下侧风面F平均风压系数云图(x=0 mm)
Figure 7. The mean pressure coefficient contour maps of surface F under different wind speeds conditions before and after applying actuation(x=0 mm)
图 8 施加激励前后不同流速下背风面E平均风压系数云图(y=96 mm)
Figure 8. The mean pressure coefficient contour maps of surface E under different wind speed conditions before and after applying actuation(y=96 mm)
图 9 不同流速下、不同布置形式激励器施加激励前后的侧风面F平均风压系数云图(x=0 mm)
Figure 9. The mean pressure coefficient contour maps of surface F under different wind speeds conditions before and after applying actuation(x=0 mm)
图 10 不同流速下、不同布置形式激励器施加激励前后的背风面E平均风压系数云图(y=96 mm)
Figure 10. The mean pressure coefficient contour maps of surfaceE under different wind speed conditions before and after applying actuation(y=96 mm)
图 11 不同布置形式激励器施加激励前后的速度标量图
Figure 11. Speed scalar quantity of the plasma actuator with different configurations before and after applying actuation
图 12 不同布置形式激励器施加激励前后的涡量图
Figure 12. Vorticity chart of the plasma actuator with different configurations before and after applying actuation
表 1 实验工况表
Table 1. Experimental conditions
激励器布置形式 风向角/(°) 来流速度/(m·s-1) 顺来流前缘激励 0 2, 3, 4, 5, 6 逆来流前缘激励 0 2, 3, 4, 5, 6, 7, 8 拐角激励 0 2, 3, 4, 5, 6, 7, 8 
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