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.
数值模拟碳氢富燃燃气与空气二维超声速剪切流动的湍流燃烧。
A turbulent combustion of hydrocarbon fuel-rich gas with air two-dimensional supersonic shear flow was numerically simulated.
用法福尔质量加权平均N-S方程及两方程湍流模型求解三维超声速平板湍流边界层流动；
The mass-weight averaging N-S equations are adopted as the governing equations of flow, and a two-equation turbulent model is employed.
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