等离子体用于三角翼模型流动控制试验研究  

Experimental investigation on delta wing flow control by plasma

作　　者：于金革[1] 牛中国[1] 梁华[2] 孙楠[1] 刘捷[1] 

机构地区：[1]中国航空工业空气动力研究院,黑龙江哈尔滨150001 [2]空军工程大学航空航天工程学院等离子体动力学重点实验室,陕西西安710038

出　　处：《空气动力学学报》2017年第2期305-309,共5页Acta Aerodynamica Sinica

摘　　要：在不同试验风速下,通过风洞天平测力试验,研究了纳秒脉冲介质阻挡放电等离子体激励频率和激励电压对三角翼模型流动控制效果的影响。研究表明:激励频率和激励电压是等离子体流动控制效果的重要影响因素,在所研究的激励频率和激励电压范围中,当激励频率f=200Hz、激励电压为13kV时,等离子体激励可有效抑制三角翼前缘涡分离,流动控制效果最佳。试验风速30m/s时,最大升力系数由1.32增大到1.45,增大9.8%,最大升阻比提高2.9%;试验风速45m/s时,最大升力系数由1.33增大到1.45,增大9.0%,最大升阻比提高0.64%。The effects of actuation frequency and actuation voltage generated by nanosecond pulse dielectric barrier discharge plasma on the flow control effects of a delta wing are investigated with different wind speeds by means of force-balance tests in the wind tunnel, the plasma actuator is installed on the delta wing. The force test results show that, actuation frequency and actuation voltage determines flow control effectivity, when the actuation frequency is 200 Hz and actuation voltage 13 kV, nanosecond pulse dielectric barrier discharge plasma inhibits the leading-edge vortices separation obviously, and the flow control effect may achieves the best . For the case of wind speed of 30m/s, the maximum lift coefficient increases 9.8% from 1.32 to 1.45, the maximum lift-drag ratio increases 2.9 %. For wind speed of 45 m/s, the maximum lift coefficient increases up to 11.2% from 1.30 to 1.45, and the maximum lift-drag ratio 0.64%.

关 键 词：纳秒脉冲 等离子体 流动控制 三角翼 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]