摘要
针对在大来流攻角下,NACA0015翼型发生的流动分离现象,在翼型吸力面前缘加装微小平板研究平板不同加装位置对翼型流动控制效果的影响。在风洞中,通过测力天平,得到翼型升阻力特性变化曲线;再通过烟线实验进行流场可视化。研究表明:当微小平板水平加装位置X=0,垂直加装位置Y=0.07c(c为翼型弦长)时,控制翼型流动控制效果最佳,失速攻角推迟了19°;在翼型前缘正前方或正上方一定距离加装微小平板,都能有效抑制翼型吸力面的流动分离,提高翼型的气动性能。
According to the flow separation at high inflow angle of attack for NACA0015 airfoil,the effect of adding a small plate to the leading edge of airfoil on its aerodynamic performance was studied by means of experimental research in this paper.The influence of different installation position of the small plate on the flow separation control of airfoil was studied with constant width and thickness of the plate.In the wind tunnel,force balance was used to obtain the lift-drag characteristic curve of airfoil,and the visualization of flow field was obtained through smoke line experiment.Results show that when the position of the small plate is X=0 and Y=0.07c,the effect of control flow is the best,and the stall angle of attack is delayed by 19°.The flow separation on the suction surface of airfoil can be effectively suppressed by installing a small plate at a certain distance in front of or above the leading edge of airfoil,and the performance of airfoil can be greatly improved.
作者
司马浩
童慧
吴兆春
黄典贵
SI MA-hao;TONG Hui;WU Zhao-chun;HUANG Dian-gui(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai,China,200093;College of Urban Construction and Safety Engineering,Shanghai Institute of Technology,Shanghai,China,201418)
出处
《热能动力工程》
CAS
CSCD
北大核心
2019年第11期116-122,共7页
Journal of Engineering for Thermal Energy and Power
基金
国家自然科学基金(51536006,51576133)
上海市科委科研计划项目(17060502300)~~
关键词
微小平板
流动控制
风洞实验
烟线法
small plate
flow control
wind tunnel experiment
smoke-wire method
