非对称翼型绕流流动机理研究  

Mechanism of Flow around Asymmetric Airfoil

作　　者：秦浩[1] 樊晓羽 李明水[3] 肖姚 QIN Hao;FAN Xiao-yu;LI Ming-shui;XIAYao(Key Laboratory of Fluid and Power Machinery,Ministry of Education,Xihua University,Chengdu,China,Post Code:610039;School of Energy and Power Engineering,Xihua University,Chengdu,China,Post Code:610039;Wind Engineering Research Center,Southwest Jiaotong University,Chengdu,China,Post Code:610031)

机构地区：[1]西华大学流体及动力机械教育部重点实验室,四川成都610039 [2]西华大学能源与动力工程学院,四川成都610039 [3]西南交通大学风工程研究中心,四川成都610031

出　　处：《热能动力工程》2020年第1期231-237,共7页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金(51278435,51408505);空气动力学国家重点实验室基金(SKLA20160205);西华大学自然科学重点基金(Z1510418);西华大学研究生创新基金(ycjj2018047)。

摘　　要：为研究翼型在均匀流情况下的绕流流动机理,采用粒子图像测速技术(PIV)对非对称翼型NACA64-418进行风洞试验,对不同攻角、不同风速下翼型绕流流场进行可视化分析,并引入涡旋强度物理量准确分析翼型表面涡脱落及再附现象,以更精确描绘流场涡结构。研究表明:当Re=1.02×10^5,攻角16°≤α<23°时,翼型表面发生再附,分离涡消失;而当攻角大于23°时,再附现象消失,临界速度随攻角的增大而减小。该试验方案及分析模型方法可以准确预测翼型表面涡脱情况,对翼型剪切层内不稳定涡旋及再附研究有着重要意义。In order to study the flow mechanism of the airfoil under uniform flow,a series of experiments on the NACA64-418 airfoil were carried out by using Particle Image Velocimetry(PIV)in an aerodynamic return flow wind-tunnel.The flow field around the airfoil at varying angles of attack and wind speed were visualized,and the swirling strength for identifying vortices was adopted to analyze the vortex shedding and reattachment of the airfoil surface and more accurately depict vortex structure.The results showed that when Re=1.02×10^5 and the angle of attack is 16°≤α<23°,the surface of the airfoil is reattached,and the separation vortex disappears.When the angle of attack is larger than 23°,the reattachment disappears,and the critical velocity decreases as the angle of attack increases.The test and analysis method can accurately predict the vortex shedding of the airfoil surface.It has important significance for the study of unstable vortex and reattachment in the airfoil shear layer.

关 键 词：翼型绕流 粒子图像测速 涡 涡旋强度 流动形态 

分 类 号：O357.5[理学—流体力学]