三角翼大迎角非对称旋涡破裂数值模拟  

Asymmetrical Vortex Breakdown of Delta Wings at High Incidence

作　　者：肖志祥[1] 陈海昕[1] 符松[1] 李凤蔚[2] 

机构地区：[1]清华大学工程力学系,北京100084 [2]西北工业大学航空学院,陕西西安710072

出　　处：《计算物理》2005年第3期221-226,共6页Chinese Journal of Computational Physics

基　　金：中国博士后科学基金;国家自然科学基金(10477012)资助项目

摘　　要：　采用由伪时间子迭代格式实现的二阶精度LU SGS方法进行时间推进,并以Jameson中心加人工粘性格式进行空间离散,应用层流假设和Baldwin Lomax(B L)模式,求解雷诺平均的薄层Navier Stokes(N S)方程组以模拟细长三角翼大迎角流动.为验证本方法,首先计算了具备实验数据的65°后掠角三角翼大迎角流场,获得令人满意的结果;然后模拟了80°后掠角的细长三角翼,研究其大迎角非对称旋涡破裂特性.A fully implicit Lower-Upper-Symmetric-Gauss-Seidel (LU-SGS) with pseudo time sub-iteration and the modified Jameson's central scheme are applied to solve thin layer Navier-Stokes (N-S) equations with laminar hypothesis and Baldwin-Lomax (B-L) model for the vortical flows around delta wings at high angles of attack (AOA). To validate the codes, a 65 degree swept delta wing is computed in transonic cases, where M∞=0.85, α=10°, 20° and Re=5×106. Then asymmetrical vortex breakdown flows with M∞=0.3, and Re=1.3×106, at high AOA around a 80° swept delta wing are presented and discussed. The computational results are compared with experimental data available and good agreement is achieved.

关 键 词：大迎角 三角翼 非对称 数值模拟 旋涡破裂 时间推进 GS方法 二阶精度 迭代格式 空间离散 人工粘性 雷诺平均 实验数据 破裂特性 后掠角 方程组 层流 求解 

分 类 号：O241.82[理学—计算数学] V211.4[理学—数学]