Experimental study on flow control of asymmetric vortex over the leeward region of the head of the slender body by sliding discharge plasma actuation
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摘要: 飞行器在大迎角飞行状态下，细长体头部背风区流场演变复杂，会出现非对称旋涡，产生随机侧向力，对飞行器的机动性和敏捷性影响很大。针对细长体大迎角非对称涡控制问题，采用顺流向布局的滑动放电等离子体激励器，结合测压和粒子图像测速（PIV）等手段，对细长体模型开展了风洞实验研究。研究结果表明：激励电压10 kV是流动控制开始生效的阈值电压；当来流速度10 m/s（雷诺数0.8×105）、迎角45°时（激励电压16 kV，归一化脉冲频率1.96），获得最佳流动控制效果，侧向力系数最高可降低83.48%；随着来流速度继续增大，流动控制效果逐渐减弱，预测在来流速度26 m/s时将完全失效。
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关键词:
- 大迎角 /
- 非对称涡 /
- 粒子图像测速（PIV） /
- 滑动放电
Abstract: When the aircraft flies at a high angle of attack, the flow field on the leeward surface of the slender body evolves in a complicated manner, and asymmetric vortices appear, generating random lateral forces, which greatly affect the maneuverability and agility of the aircraft. In order to solve this problem, a sliding discharge plasma actuator with an along-stream layout was used to conduct wind tunnel experiments on a slender body model, combined with pressure measurement and particle image velocimetry（PIV）. The experimental results show that the actuation voltage of 10 kV is the threshold voltage at which the flow control starts to take effect. When the velocity of the incoming flow is 10 m/s（Re=0.8×105）, the angle of attack is 45°, and the actuation voltage is 16 kV, the best flow control effect can be achieved at the normalized pulse frequency of 1.96, the lateral force coefficient can be reduced by 83.48%. However, as the flow velocity increases, the flow control effect becomes weaker gradually and is expected to disappear at 26 m/s. -
图 4 滑动放电等离子体激励器示意图及实物图
Figure 4. Schematic diagram and image of sliding discharge plasma actuator
图 5 不同激励电压下的细长体表面压力分布
Figure 5. The pressure distribution with different actuation voltages
图 6 不同激励电压下的等离子体流动控制PIV测量结果
Figure 6. PIV measurement plasma flow control results at different actuation voltages
图 7 不同来流速度下的压力分布对比
Figure 7. Comparison of pressure distributions at different wind speeds
图 8 不同来流速度下的等离子体流动控制PIV测量结果
Figure 8. PIV measurement results of plasma flow control with different incoming wind speeds
表 1 不同激励电压对侧向力控制的影响分析
Table 1. Analysis of the influence of different actuation voltages on lateral force control
Up-p/kV CC ΔCC η 0 0.643 0 0 8 0.638 0.005 0.78% 10 0.576 0.067 10.42% 12 0.493 0.150 23.33% 14 0.325 0.318 49.46% 16 0.108 0.535 83.20% 
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表 2 不同来流速度对侧向力控制的影响分析
Table 2. The influence of different wind speeds on lateral force control
u∞ Plasma off Plasma on ΔCC η 10 0.454 0.075 0.379 83.48% 15 0.471 0.215 0.256 54.35% 20 0.503 0.356 0.147 29.22% 25 −0.605 −0.569 0.036 5.95%
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