PROGRESS IN THE RESEARCH OF HYPERSONIC AND HIGHENTHALPY BOUNDARY LAYER INSTABILITIES AND TRANSITION
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摘要: 边界层由层流向湍流的转捩是高超声速飞行器设计面临的重大空气动力学问题. 随着飞行速域与空域的不断拓展, 高超声速高焓边界层中的高温气体效应会使得量热完全气体假设失效, 从而深刻影响流动转捩过程. 相关研究涉及多个学科, 是典型的多物理场耦合问题. 近年来, 随着相关飞行器技术的快速发展, 高超声速高焓边界层转捩问题的重要性越来越得到体现, 相关研究已成为国际上的热点领域. 本文综述相关研究进展, 首先介绍目前常用的高温气体物理模型, 尤其关注热化学非平衡模型, 并介绍激波捕捉、激波装配和边界层方程解等常用的高焓流动求解方法, 以及相关风洞和飞行试验技术的进展. 然后综述高温气体效应对转捩过程中的感受性、模态增长、瞬态增长和非线性作用等的影响的相关研究, 其中流向不稳定性中出现较大增长率的第三模态和超声速模态引起了广泛的研究兴趣. 最后进行总结, 并对未来发展略作展望.Abstract: Boundary layer transition from laminar to turbulence is of vital importance to the design of hypersonic vehicles. With continuous expansion of flight speed and altitude domains, the high-temperature gas effects in hypersonic high-enthalpy boundary layers invalidate the calorically perfect gas assumption. They can thus largely influence the flow transition process. Relevant research is multi-interdisciplinary and multi-physics coupling. In recent years, the hypersonic high-enthalpy boundary layer transition has received increasing interest worldwide owing to rapid development of vehicle design. Recent progress is reviewed in this article. Firstly, commonly used high-temperature gas models are introduced, especially the thermochemical non-equilibrium models. Then, the prevailing computational methods for high-enthalpy flows, including the shock-capturing, shock-fitting and boundary layer equation methods are introduced. The progress in experimental techniques for high-enthalpy wind tunnels and flight tests are also summarized. Afterward, the influences of high-temperature effects on the receptivity, modal growth, transient growth and nonlinear interactions in the transition process are reviewed. Here some phenomena has received wide interests that the third mode and the supersonic mode appear at relatively large growth rates in the streamwise instability. Finally, the progress is summarized, and future researches are briefly prospected.
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图 6 式(4)给出的
$ \mathrm{\varDelta } $ 的等值线Figure 6. Contours of
$ \mathrm{\varDelta } $ (unit in meter) from Eq. (4)
图 7 10马赫绝热平板边界层算例中(a)流向速度, (b)温度和振动温度和(c)氧气质量分数的剖面(
$ {Re}_{\delta } $ = 2000)Figure 7. (a) Streamwise velocity, (b) temperature and vibrational temperature and (c) oxygen mass fraction profiles in a Mach-10 adiabatic flat-plate boundary layer flow
图 12 10马赫绝热平板边界层中二维模态的(a)增长率和(b)相速度随圆频率的变化(
$ {Re}_{\delta } $ = 2000)Figure 12. (a) Growth rate and (b) phase velocity of the 2D mode in a Mach-10 adiabatic flat-plate boundary layer
表 1 热化学非平衡效应对第二模态的影响汇总
Table 1. Summary of the influences of TCNE effects on the second mode
Boundary layer change On the second mode Key parameters on the base flow (effect I) lower temperature and density, lower speed of sound higher growth rate, higher frequency $ {Da}_{v}^{\mathrm{b}\mathrm{a}\mathrm{s}\mathrm{e}}\propto \dfrac{1}{{Re}_{x}} $ on the disturbance (effect II) lower speed of sound (with base flow unchanged) higher growth rate, lower frequency $ {Da}_{v}^{\mathrm{d}\mathrm{i}\mathrm{s}\mathrm{t}}\propto \dfrac{1}{\sqrt{{Re}_{x}}} $ disturbance amplitude dissipation (endothermic processes) lower growth rate 
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