马赫数为6的高超声速钝锥湍流边界层空间演化的直接数值模拟  

Direct numerical simulation of a spatially evolving hypersonic blunt cone turbulent boundary layer at Mach 6

作　　者：董明[1] 

机构地区：[1]天津大学力学系,天津300072

出　　处：《空气动力学学报》2009年第2期199-205,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学重点基金资助项目(10632050);国家自然科学重大研究计划项目(90716007);全国优博论文(200328)

摘　　要：首先求解了来流马赫数为6的零攻角高超声速钝锥边界层的层流基本流场,在选定的计算域入口引入一组有限幅值的T-S波扰动,用高精度差分格式对流动进行了直接数值模拟。引入的扰动触发了转捩,从而得到了空间模式下的湍流边界层。研究了湍流平均场与脉动场的统计特性,给出了相干结构的流动显示图,并对强雷诺比拟的结论进行了检验。The laminar basic flow of a hypersonic blunt cone boundary layer with zero angle of attack, at oncoming Mach number 6, was calculated firstly, and then, a group of T-S wave disturbances with finite amplitude was introduced at the entrance of the computational domain selected, the direct numerical simulation （DNS） was performed with high order difference scheme being employed. The disturbances introduced burst out transition, thereby, the turbulent boundary layer with spatial mode was obtained. The statistical characteristic of the turbulent mean field and fluctuation field was studied, the visualization of the coherent structure was shown, and the conclusion of Strong Reynolds Analogy was scaled.

关 键 词：高超声速钝锥边界层 湍流边界层 直接数值模拟 

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]