Asymmetric Flow Control on a Delta Wing with Dielectric Barrier Discharge Actuators
Asymmetric Flow Control on a Delta Wing with Dielectric Barrier Discharge Actuators
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DOI：
10.2514/1.j054373
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发表时间：
2016-02
期刊：
影响因子：
2.5
通讯作者：
Lu Shen;C. Wen;Hsin-An Chen
中科院分区：
文献类型：
--
作者：
Lu Shen;C. Wen;Hsin-An Chen
本文介绍了介质阻挡放电等离子体激励器对75 °后掠角三角翼前缘涡流控制效果的实验研究。基于三角翼弦的雷诺数为50，000。风洞中的烟流显示和粒子图像测速实验表明，介质阻挡放电等离子体激励器引起的非对称控制可以显著影响三角翼上的整体流场结构：激励器同侧前缘涡破裂位置提前，而另一侧前缘涡破裂位置延迟。这一现象是首次观察到的，并且仅在当前的全展三角翼实验中观察到，与半展实验的结果有显著差异。测力结果表明，非对称控制对升力产生的贡献有限，但会产生较大的滚转力矩。
This paper presents an experimental investigation of the effect of the dielectric barrier discharge plasma actuators on the leading-edge vortex flow control over a delta wing with a 75 deg swept angle. The Reynolds number based on the delta wing chord is 50,000. The smoke flow visualization and particle image velocimetry experiments in the wind tunnel indicate that the asymmetric control caused by the dielectric barrier discharge plasma actuator can significantly affect the global flow structure over the delta wing: the leading-edge vortex breakdown position on the same side of the actuator is advanced, whereas vortex breakdown on the other side is delayed. This phenomenon is observed for the first time and is only observed in the current full-span delta wing experiment, significantly different from the result of the semispan experiment. The force measurement result shows that the asymmetric control has a limited contribution to lift generation but can induce a relatively large roll moment.