不同网格拓扑对细长体绕流计算的影响研究  

Effect of Different Grid Topology on the Calculation of Flow around a Slender Body

作　　者：刘跃[1] 管小荣[1] 徐诚[1] 常玲玲[2] 

机构地区：[1]南京理工大学机械工程学院,江苏南京210094 [2]宁夏大学数学计算机学院,宁夏银川750021

出　　处：《力学季刊》2016年第2期318-326,共9页Chinese Quarterly of Mechanics

基　　金：国家自然科学基金(11202101)

摘　　要：分别运用扇形(Fan)、阶梯形(Ladder)、交界面形(Interface)网格对细长体小攻角对称、大攻角对称、大攻角非对称绕流流场进行了数值研究.通过涡核位置、涡簇显示、物面压力分布、轴向力分布等的计算结果比较了三种网格的计算精度.数值实验表明:细长体分离涡流场对边界层网格非常敏感,应严格控制边界层网格的正交性;随着攻角增大,流场对网格特性的敏感性有增高的趋势;阶梯形网格可能会对流场带入非物理性扰动,交界面网格对流场捕捉有不连续现象;将三种网格得到的物面压力、侧向力、流动分离位置与实验值进行对比,发现扇形网格误差最小、交界面网格误差最大;大攻角非对称流动时,扇形网格计算的侧向力有整体向细长体头部压缩的趋势,涡脱落位置靠前,第二个及第三个极值更大,说明非对称现象有向尾部发展的趋势.The symmetric vortex flows over a slender body at low and high incidence are numerically simulated using Fan grid, Ladder grid, and Interface grid. The asymmetric vortex flow at high incidence is also investigated. From the comparisons of vortex core location, vortex visualizations, surface pressure, and force along the length, it is confirmed that the separated flow around the slender body is very sensitive to the grid of boundary layer. It is necessary to strictly ensure the grid orthogonality; With the increase of incidence, the flow shows more sensitive to the grid; The ladder grid may arouse Non-physical disturbance in the flow, and the vortex visualizations of interface grid has a discontinuous phenomena; The calculation error for surface pressure, tbrce along the length and separation location using Fan grid is minimum, and that using interface grid is maximum; The force along the length using Fan grid has a compression trend to the head of the slender body, with the float location closer to the head. The second and third extreme values are larger, indicating that the asymmetry flow using Fan grid has a trend of extending to the rear of the slender body.

关 键 词：流体力学 细长体 分离流 网格 数值模拟 

分 类 号：TJ011.2[兵器科学与技术—兵器发射理论与技术] V211.3[航空宇航科学与技术—航空宇航推进理论与工程]