基于重叠网格的翼型动态失速数值模拟  

Numerical Simulation of Dynamic Stall of Airfoil Based on Overset Grids

作　　者：张团元 夏润泽 刘书岩 员海玮[2] ZHANG Tuan-yuan;XIA Run-ze;LIU Shu-yan;YUN Hai-wei(Naval Aviation University,Yantai Shandong 264001,China;State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing Jiangsu 210016,China)

机构地区：[1]海军航空大学,山东烟台264001 [2]南京航空航天大学机械结构力学及控制国家重点实验室,江苏南京210016

出　　处：《计算机仿真》2023年第8期114-119,共6页Computer Simulation

摘　　要：由于动态失速的相关特性及网格变形方法的限制性,采用重叠网格方法及广泛应用在分离流动问题中的SST k-ω湍流模型对NACA0012翼型开展了非定常动态失速的数值模拟研究,得到了动态运动过程中的气动力系数及翼型周围的流线图。研究结果表明采用的计算网格及方法不仅可以有效模拟翼型小幅振荡的动态特性,对大迎角俯仰运动的计算也具有良好的效果。同时能够精确的模拟出俯仰振荡过程中的气动力迟滞效应及大迎角动态失速时翼型前缘涡产生、脱落到再附的运动过程。Due to the characteristics of dynamic stall and the limitation of the grid deformation method,this paper used the method of overset grids and the SST k-ω turbulence model,which is widely used in separated flow problems,to carry out the numerical simulation of the unsteady dynamic tall on the NACA0012 airfoil.And the aerodynamic coefficients and streamline diagrams around the airfoil were obtained.The results show that the grid and method can not only effectively simulate the dynamic characteristics of airfoil small oscillations,but also have a goodeffecton the calculation of pitching motion at high angle of attack.At the same time,it can accurately simulate the aerodynamic hysteresis effect in the process of pitching oscillation and the motion process of airfoil leading-edge vortex generation,shedding and reattachment in the process of dynamic stall.

关 键 词：计算空气动力学 重叠网格 动态失速 俯仰振荡 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]