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Experimental study on evolution characteristics of plane subsonic-supersonic shear layer
Aerospace Science and Technology ( IF 5.0 ) Pub Date : 2020-02-20 , DOI: 10.1016/j.ast.2020.105791
Kai Ma , Jiang Li , Qiang Li , Yang Liu

The study of plane subsonic-supersonic shear layer formed by the subsonic ramjet air and the supersonic rocket jet in the rocket based combined cycle is of profound significance for analyzing the mixing characteristics in combustor. In this study, the mixing features including vortex structures, growth rate and evolution characteristics of pressure unmatched subsonic-supersonic shear layer were experimentally investigated using the ice-cluster based planar laser scattering technique and the subsonic-supersonic shear layer test device. The convective Mach number ranges from 0.38 to 0.73, and the corresponding pressure deviation between both flows is 0 to 32.4%, respectively. Results show that the experimental and theoretical normalized growth rates agree well with each other for the pressure matched case. The pressure mismatch effect could make the shear layer transition in advance and the shear layer deflects to the lower pressure side. And that the deflection angle and the deviation of normalized growth rate are positively correlated with the pressure deviation. Therefore, the pressure mismatch effect could suppress the growth of shear layer even though amending the convective Mach number using the parameters after the expansion wave induced by the pressure mismatch.



中文翻译:

平面亚音速-超音速剪切层演化特征的实验研究

在基于火箭的联合循环中研究亚音速冲压空气和超音速火箭喷气形成的平面亚音速-超音速剪切层,对于分析燃烧室的混合特性具有重要的意义。本研究利用基于冰团的平面激光散射技术和亚音速-超音速剪切层试验装置,对压力分布不匹配的亚音速-超音速剪切层的涡旋结构,生长速率和演化特征进行了实验研究。对流马赫数的范围为0.38至0.73,两次流动之间的相应压力偏差分别为0至32.4%。结果表明,在压力匹配的情况下,实验和理论上的标准化增长率彼此吻合良好。压力失配效应可能会使剪切层提前转变,并且剪切层会偏向低压侧。并且偏转角和归一化增长率的偏差与压力偏差正相关。因此,即使使用由压力失配引起的膨胀波之后的参数来修改对流马赫数,压力失配效果也可以抑制剪切层的生长。

更新日期:2020-02-20
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