应用加权紧致非线性格式的VFE-2钝前缘三角翼转捩模拟  

Numerical simulation on VFE-2 rounded leading edge delta wing using weighted compact nonlinear scheme

作　　者：王光学[1,2] 王圣业 王东方[1] 邓小刚[1] 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073 [2]中山大学物理学院,广东广州510006

出　　处：《国防科技大学学报》2016年第4期8-13,共6页Journal of National University of Defense Technology

基　　金：国防科学技术大学科研计划资助项目(ZDYYJCYJ20140101)

摘　　要：为研究前缘转捩对钝前缘三角翼涡结构的影响,采用高阶精度加权紧致非线性格式和γ-Reθ转捩模型对VFE-2中等半径钝前缘三角翼进行数值模拟。将计算结果与试验结果进行详细对比,结果表明:钝前缘三角翼的前缘分离涡发生在翼尖下游,在特定雷诺数下其具体发生位置受转捩因素影响,采用全湍流模型计算会推迟分离,而耦合转捩模型后的计算结果和试验结果吻合良好。运用耦合转捩模型方法,对钝前缘三角翼涡结构随迎角变化进行模拟。计算结果与试验结果吻合,表明在较小的迎角下,前缘不会产生分离诱导涡;随迎角不断增大,分离诱导涡在三角翼后缘附近产生并向上游移动。In order to evaluate the influence of transition on the vortex structure of delta wing, a numerical simulation of VFE - 2 rounded leading edge delta wing was carried out by using a high-order scheme-weighted compact nonlinear scheme and the y - Red transition model. A comparisons between calculated results and experiment data indicate that the leading edge vortex begins at a certain distance of the wing apex and the transition has great influence on the onset of leading edge vortex. Using turbulence model without transition, the leading edge separation is delayed much, while with transition model the calculated results show a good agreement with experiment data. With transition model, numerical simulation on VFE - 2 rounded leading edge delta wing at variation of the angle-of-attack was carried out. The calculated results which agree well with experiment data show that at a low angle-of-attack, there is no separation-induced leading-edge vortex, but with the increase of angle-of-attack the leading edge separation displays being closer to the trailing edge and moves upstream.

关 键 词：转捩模型 三角翼 高精度格式 加权紧致非线性格式 分离诱导涡 

分 类 号：TN95[电子电信—信号与信息处理]