沟槽表面对翼型绕流流场的气动作用研究  

Research on aerodynamic effects of groove surface on the airfoil flow field

作　　者：陈子龙 杨爱玲[1] 陈二云[1] 焦跃 CHEN Zilong;YANG Ailing;CHEN Eryun;JIAO Yue(School of Energy and Power Engineering/Shanghai Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093,China)

机构地区：[1]上海理工大学能源与动力工程学院/上海市动力工程多相流动与传热重点实验室,上海200093

出　　处：《能源研究与信息》2021年第3期160-168,175,共10页Energy Research and Information

基　　金：国家自然科学基金资助项目(51106099、11502146);上海市科委科研计划项目(13DZ2260900)。

摘　　要：基于大涡模拟(LES)技术对NACA6510翼型二维绕流流场进行数值模拟,研究吸力面圆弧型沟槽相对位置、相对深度对翼型气动特性与涡流结构的影响规律。研究表明:在小攻角下,沟槽表面对翼型的升、阻力系数影响很小,在大攻角下升、阻力系数明显减小。气体流经沟槽结构时会在内部形成反向二次漩涡,其脉动主频为上、下游主频的2倍,相对深度不同其内部漩涡特性呈现不同规律。在一定条件下,沟槽涡流失稳,存在周期性的涡流产生、发展和脱落,翼型尾缘保持了上游及沟槽内压强脉动的频率特性,脉动幅值逐渐增强。随着沟槽深度的增加,翼型尾缘压强脉动幅值呈先降后升的分布趋势。沟槽较浅时,沟槽的存在对频率特性的影响不明显;沟槽达到一定深度后,压强脉动频率发生突变且明显降低。Numerical simulation of two-dimensional flow field around NACA6510 airfoil was conducted based on large eddy simulation(LES)method.The influence of the relative position x/c and the relative depth h/λof arc-shaped groove at the suction surface on the aerodynamic characteristics and vortex structure of the airfoil was studied.The results show that under the small angle of attack,the groove surface has little influence on the lift and drag coefficient of the airfoil,which however is significantly reduced at the large angle of attack.A reverse secondary vortex occurred when the air flows across the groove,whose main fluctuation frequency is twice large of that at its upstream and downstream.The groove structure with different h/λcauses different vortex characteristics.Under certain conditions,the eddy is unstable.And periodic vortex generates,develops,and falls off.The frequency profile of pressure fluctuation at the trailing edge is the same as those at its upstream and in the groove.And the fluctuation amplitude gradually increases.With the increase of the groove depth,the pressure fluctuation amplitude at the trailing edge of the airfoil shows a downward trend and then an upward one.The groove with small depth has no obvious effect on the frequency profile.When the groove depth reaches a certain level,the pressure fluctuation frequency varies suddenly and decreases significantly.

关 键 词：沟槽 翼型 气动特性 二次涡 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]