Abstract

This paper is devoted to understanding gasdynamic liquid drops breakup in a supersonic flow with presence of an oblique shock wave. An experimental facility, diagnostic tools and an experimental methodology are presented as well as numerical simulations results. Computations and experiments were used to get flow parameters in the duct with supersonic flow at Mach numbers 2.0, 2.5, and 3.0. The droplets were made to interact with a single oblique shock wave generated by a wedge in the test section. Experimental data are obtained for the change in diameter of the droplets and the change in speed of droplets in a supersonic flow at the three Mach numbers. The data are presented for an initial Weber number over the range of 16–115. It is shown that the mass loss rate of droplets are quadratically related to the Weber number, irrespective of the presence of oblique shock.

中文翻译：

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倾斜冲击波在超音速流中气动力液滴破裂的实验研究

摘要

本文致力于了解在倾斜冲击波的存在下超声速流动中的气体液滴破裂。介绍了实验设备，诊断工具和实验方法以及数值模拟结果。使用计算和实验来获得马赫数为2.0、2.5和3.0的超音速流道中的流场参数。使液滴与由测试部分中的楔形产生的单个倾斜冲击波相互作用。获得了三个马赫数下的超声流中液滴直径的变化和液滴速度变化的实验数据。给出的数据为初始Weber数，范围为16-115。结果表明，液滴的质量损失率与韦伯数呈平方关系，