通过综述可知，超声速混合层燃烧研究仍需开展大量工作。
The review suggests that a large amount of research work on combustion in supersonic mixing layers still needs to be conducted.
在对流马赫数为1.24的超声速湍流混合层风洞中，以NPLS实验技术为基础观察到了小激波结构。
The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24.
本项目利用数值模拟手段，对超声速剪切层混合增强的新方法进行了探索。
In this project, some new techniques to enhance supersonic mixing layer are studied by the numerical method.
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