等离子体控制翼型流动分离实验  

Experiment investigation on airfoil separation control by plasma

作　　者：方弘毅[1] 李光里[1] 杨波[2] 

机构地区：[1]沈阳航空航天大学动力与能源工程学院,辽宁沈阳110136 [2]大连海事大学环境工程研究所,辽宁大连116026

出　　处：《沈阳航空工业学院学报》2010年第4期18-22,共5页Journal of Shenyang Institute of Aeronautical Engineering

基　　金：国家自然科学基金项目(项目编号:60801010)

摘　　要：为了提高等离子体的流动控制能力,在常规大气环境,来流风速分别为20m/s、30m/s、40m/s条件下进行了介质阻挡放电抑制NACA0015翼型流动分离实验研究。结果表明:等离子体能有效的抑制分离,实现增升减阻,但随着来流风速增加,有效控制的起始和终止攻角均变大,攻角区域却逐渐变小;可以通过在翼型分离点附近布置等离子体激励器,在允许的范围内尽量提高输入功率,使控制效果达到最佳。Experimental investigation on the NACA0015 airfoil flow separation suppression by dielectric barrier discharge is performed to improve the flow control capability of plasma under normal atmosphere environment with the free-stream velocity of 20m/s,30m/s and 40m/s.Experimental results indicate that the plasma can effectively suppress the flow separation,realize lifts augmentation and drag reduction.As the inflow speed increased,the start and end angle of attack with effective control have become larger and the angle of attack region has gradually become more smaller.Near the separation point,the flow is very sensitive to the input energy,therefore,the best control effect can be obtained by arranging the plasma actuator near the separation point of airfoil and maximizing the input power of the actuator in an allowed range.

关 键 词：航空航天推进系统 流动控制 介质阻挡放电 等离子体 流动分离 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]