高超音速零攻角尖锥边界层转捩的机理

基金项目: 国家自然科学基金(重点)资助项目(10632050)

Mechanism of Transition in a Hypersonic Sharp Cone Boundary Layer With Zero Angle of Attack

摘要: 先计算出高超音速零攻角尖锥边界层的定常层流流场．然后在计算域的入口引入两组有限幅值的T-S波扰动，对空间模式的转捩过程进行了直接数值模拟．分析了转捩过程的机理，发现平均流剖面稳定性的变化是其关键．并进一步讨论了不同模态初始扰动在高超音速尖锥边界层中的演化规律．
- 零攻角 /
- 尖锥边界层 /
- 转捩 /
- 稳定性
Abstract: Firstly,the steady laminar flow field of a hypersonic sharp cone boundary layer with zero angle of attack was computed.Then two groups of finite amplitude T-S wave disturbances were introduced at the entrance of the computational field,and the spatial mode transition process was studied by direct numerical simulation(DNS).The mechanism of the transition process was analyzed.It was found that the change of the stability characteristics of the mean flow profile was the key issue.Moreover,the characteristics of evolution for the disturbances of different modes in the hypersonic sharp cone boundary layer was discussed.
- zero angle of attack /
- sharp cone boundary layer /
- transition /
- stability

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