Crossflow instability in a hypersonic boundary layer
Crossflow instability in a hypersonic boundary layer
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DOI：
10.1017/jfm.2016.643
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发表时间：
2016-10
影响因子：
3.7
通讯作者：
Stuart A. Craig;W. Saric
中科院分区：
文献类型：
--
作者：
Stuart A. Craig;W. Saric
本文首次用边界层内点测量方法研究了高超声速层流边界层中的横流不稳定性。实验是在得克萨斯A&M大学低扰动马赫数6静风洞中，在一个7°直角圆锥体上进行的，绝热壁面条件为5.6°。测量是用一个恒温热线风速仪系统，频率响应高达180千赫。稳定的横流波被观察到增长和饱和。行波与驻波共存，并出现在以35 kHz为中心的频带中。在以110 kHz为中心的频带中也观察到I型二次不稳定性。所有三种模式的行为在很大程度上是一致的，与他们的低速对应物之前的驻波饱和。之后，行为仍然与低速情况部分一致。在这项研究中既没有观察到II型二次不稳定，也没有过渡到湍流。
The crossflow instability in a hypersonic, laminar boundary layer is investigated using point measurements inside the boundary layer for the first time. Experiments are performed on a 7° right, circular cone with an adiabatic wall condition at 5.6° angle of incidence in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University. Measurements are made with a constant-temperature hot-wire anemometer system with a frequency response up to 180 kHz. Stationary crossflow waves are observed to grow and saturate. A travelling wave coexists with the stationary wave and occurs in a frequency band centred around 35 kHz. A type-I secondary instability is also observed in a frequency band centred around 110 kHz. The behaviour of all three modes is largely consistent with their low-speed counterparts prior to saturation of the stationary wave. Afterward, the behaviour remains in partial agreement with the low-speed case. Neither type-II secondary instability nor transition to turbulence are observed in this study.