脉冲等离子体激励控制翼型动态失速风洞试验研究
Experimental Study on Dynamic Stall of Airfoil Controlled by Pulsed Plasma Actuation in Wind Tunnel
杨鹤森 1梁华 1吴云 2赵光银3
作者信息
- 1. 空军工程大学 等离子体动力学重点实验室,陕西 西安 710038
- 2. 空军工程大学 等离子体动力学重点实验室,陕西 西安 710038;西安交通大学 高电压技术教研室,陕西 西安 710049
- 3. 中国空气动力研究与发展中心 旋翼空气动力学重点实验室,四川 绵阳 621000
- 折叠
摘要
为探索毫秒脉冲等离子体激励(AC-DBD)和纳秒脉冲等离子体激励(NS-DBD)控制翼型动态失速的效果,本文开展了SC-1095旋翼翼型的动态失速风洞试验研究.首先,基于雷诺数为6.5×105的静态翼型失速特性,设置了动态失速试验的状态.在翼型动态失速试验中,保持来流速度U∞=30m/s、翼型运动规律α(t)=16°+8°sin(ωt)不变,分别在相同激励参数组合和相同功率输入条件下,对比了毫秒脉冲和纳秒脉冲等离子体气动激励控制翼型动态失速的效果.研究发现在试验设置的参数条件下,毫秒脉冲和纳秒脉冲激励均能减小翼型动态升力迟滞回线的面积,减小低头力矩并改善阻力特性;但无论是在相同的激励参数组合下还是在相同功率输入的条件下,纳秒脉冲激励的控制效果均优于毫秒脉冲激励,这体现了纳秒脉冲激励在控制翼型动态失速中的优势.
Abstract
In order to explore the effect of AC-DBD and NS-DBD actuation on dynamic stall control of airfoil,a wind tunnel experiment based on SC-1095 airfoil was designed.First,based on the static airfoil stall characteristics with Reynolds number of 6.5×105,the dynamic stall state was set.In the dynamic stall experiment of airfoil,the inflow velocity U∞=30m/s and the movement profile of airfoil α(t)=16°+8°sin(ωt)kept unchanged.The results of dynamic stall controled by AC-DBD and NS-DBD actuation were compared under the same actuation parameter combination and the same power input conditions.It is found that both AC-DBD and NS-DBD actuation can reduce the area of the dynamic lift hysteresis loop of the airfoil,reduce the nose-down moment and improve the resistance characteristics under the parameters set by the experiment.However,the control effect of NS-DBD actuation is better than that of AC-DBD actuation under the same actuation parameter combination or the same power input,which reflects the advantage of NS-DBD actuation in the control of dynamic stall of airfoil.
关键词
翼型动态失速/等离子体/脉冲激励/流动控制/风洞试验Key words
airfoil dynamic stall/plasma/pulsed actuation/flow control/wind tunnel experiments引用本文复制引用
出版年
2024
NETL
NSTL
万方数据