基于Richardson外推法的CFD离散误差分析  

Analysis of CFD Discrete Error Based on Richardson Extrapolation Method

作　　者：左玲玉 司海青[1] 李耀[1] 仇静轩 李根 吴晓军[2] 赵炜 ZUO Ling-yu;SI Hai-qing;LI Yao;QIU Jing-xuan;LI Gen;WU Xiao-jun;ZHAO Wei(College of General Aviation and Flight,Nanjing University of Aeronautics and Astronautics,Nanjing 211100;China Aerodynamics Research and Development Center, Mianyang 621000, China)

机构地区：[1]南京航空航天大学通用航空与飞行学院,江苏南京211100 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《指挥控制与仿真》2022年第1期58-62,共5页Command Control & Simulation

基　　金：南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20200702);江苏省研究生科研与实践创新计划(KYCX20_0214)。

摘　　要：为研究数值模拟中网格类型及网格尺度变化对离散误差产生的影响,对NACA2412三维翼型在0°、4°、8°、12°攻角下进行了计算流体力学(CFD)仿真,得到了对应条件下的升力系数及阻力系数,利用Richardson外推法研究多套连续变化的结构网格及非结构网格数值解的空间离散误差,并结合网格收敛指标(GCI)法对误差进行分析,最后,通过网格收敛性分析得到对应网格研究组修正后的精确解。结果表明:各个攻角条件下结构网格模型的离散误差均明显小于非结构网格,网格类型的改变对升力系数的影响更大,且细网格模型具有更好的网格收敛性。In order to study the influence of grid type and grid scale changes on the discrete error in the numerical simulation,CFD simulation is performed on the NACA2412 three-dimensional airfoil at 0°,4°,8°and 12°angles of attack,and the lift coefficient and drag coefficient under corresponding conditions are obtained.The Richardson interpolation method is used to study the spatial discretization errors of multiple sets of continuously changing structured grids and unstructured grids.The grid convergence index(GCI)method is used to analyze the error.Finally,the modified exact solution of the corresponding grid research group is obtained by grid convergence analysis.The results show that the discrete errors of the structured grid model are significantly less than those of the unstructured grid under the conditions of various angles of attack.The change of the mesh type has a greater impact on the lift coefficient,and the fine mesh model has better mesh convergence.

关 键 词：计算流体力学 NACA2412 离散误差 RICHARDSON外推法 网格收敛指标 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]