A Computational Estimation of Velocity Distribution of Boundary Layer on a Spherical Bubble

Hiroaki Kusuno, T. Sanada
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Abstract

The aim of this study is to investigate a velocity distribution of velocity boundary layer on a spherical bubble using numerical simulation and to compare the results with the theoretical model. In this study, we calculated the axisymmetric flow around a spherical bubble, the Reynolds number ranged from 50–1000. We selected Navier-Stokes equations written in the vorticitystream function to capture small vorticity generated on the bubble surface. We described bubble surface with boundary-fitted coordinate system. As a preliminary test, we guaranteed the accuracy of calculation method adopted in this study. Previous study showed that it needs three calculation points in the theoretical boundary layer to describe the boundary layer with second order accuracy. Our study, however, shows that the it needs seven points to describe the boundary layer even if forth order accuracy. We compared the velocity distribution of numerical result to that of theoretical model. The velocity in the vicinity of bubble is divided into potential solution and perturbed velocity component. At bubble side, the absolute value of the perturbation velocity estimated by numerical result is slightly larger than that of the theoretical model in any Reynolds numbers. When we defined bubble boundary layer thickness as the region below to 99% velocity of the potential solution, we find that value of the boundary layer thickness proposed in this study is two to three times larger than that of theoretical model. In the vicinity of the rear stagnant region (i.e. in the wake of bubble), numerical and the theoretical velocity distribution does not match at all.
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球形气泡边界层速度分布的计算估计
本文利用数值模拟方法研究了球形气泡上速度边界层的速度分布,并与理论模型进行了比较。在本研究中,我们计算了围绕球形气泡的轴对称流动,雷诺数范围为50-1000。我们选择写在涡度流函数中的Navier-Stokes方程来捕捉气泡表面产生的小涡度。用边界拟合坐标系描述气泡表面。作为初步试验,我们保证了本研究采用的计算方法的准确性。以往的研究表明,要实现对边界层的二阶精度描述,需要理论边界层中的三个计算点。然而,我们的研究表明,即使有四阶精度,也需要七个点来描述边界层。将数值结果与理论模型的速度分布进行了比较。将气泡附近的速度分为势解和摄动速度分量。在任意雷诺数下,数值结果估计的气泡侧扰动速度绝对值略大于理论模型。当我们将气泡边界层厚度定义为低于势解速度99%的区域时,我们发现本文提出的边界层厚度值比理论模型大2 ~ 3倍。在后滞流区附近(即气泡尾迹处),数值速度分布与理论速度分布完全不匹配。
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