SPH方法气-液界面边界条件研究

发布时间：2018-11-26 16:35

【摘要】：针对界面附近粒子光滑函数截断和非物理穿透问题,提出一种气-液界面边界条件的处理方法.当界面附近支持域出现不同材料粒子,每步计算可在支持域设置虚粒子,按照密度分配方法给虚粒子物理量赋值,并对界面附近粒子引入气-液两相阻力.采用SPH方法和Level-Set方法,计算运动激波对气-液界面作用问题,两者计算结果一致,初步验证了气-液界面边界条件处理的适用性.用SPH方法分别计算超声速气流中的圆截面液柱绕流和下落问题,界面两侧粒子压力和法向速度连续,给出弓形激波、回流区和下游回流区等定性合理结果.表明本文方法可适度避免界面附近流体粒子光滑截断和粒子非物理穿透现象、界面附近流场数值振荡.
[Abstract]:To solve the problem of truncation of particle smooth function and non-physical penetration near the interface, a method for dealing with the boundary conditions of gas-liquid interface is proposed. When different material particles appear in the support region near the interface, virtual particles can be set up in each step in the support domain, the physical quantities of the virtual particles can be assigned according to the density distribution method, and the gas-liquid two-phase resistance is introduced to the particles near the interface. The SPH method and the Level-Set method are used to calculate the interaction of moving shock waves on the gas-liquid interface. The results are in agreement with each other, which preliminarily verifies the applicability of the treatment of the gas-liquid interface boundary conditions. The SPH method is used to calculate the flow and fall of circular cross section liquid column in supersonic airflow respectively. The particle pressure and normal velocity on both sides of the interface are continuous. The qualitative and reasonable results of bow shock wave, reflux region and downstream reflux zone are given. It is shown that the proposed method can avoid the phenomena of smooth truncation of fluid particles near the interface and non-physical particle penetration and numerical oscillation of the flow field near the interface.
【作者单位】：清华大学航天航空学院;
【基金】：博士后基金(2015M581081) 中国运载火箭技术研究院基金(CALT201601) 清华大学自主课题(20161080102)资助项目
【分类号】：O35

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