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中文摘要：
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，在选定的计算域人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。
英文摘要：
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.
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