热力学非平衡状态下DSMC绝热壁边界的抽样方法  

A New Sampling Method of Adiabatic Boundary Condition in DSMC under Thermodynamic Non-Equilibrium

作　　者：黄飞[1] 赵波[1] 程晓丽[1] 沈清[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《宇航学报》2013年第11期1451-1455,共5页Journal of Astronautics

基　　金：国家自然科学基金(11172284)

摘　　要：从直接模拟蒙特卡罗仿真DSMC方法的实现途径出发,经过分析推导,给出了一种在考虑分子转动能、振动能等热力学非平衡状态下统计求解绝热壁温的DSMC抽样方法。然后采用锥体外形的算例验证,分析了该方法在实现绝热壁条件时的统计误差。计算结果表明,此种方法能够有效地实现DSMC方法壁面处的绝热壁条件,随着采样步数的增加,其边界条件实现时的统计误差不断降低,该方法收敛后的统计误差可降至0.5%,能够满足工程要求。A new sampling solution method of adiabatic boundary condition based on an iterative process in DSMC is introduced by analyzing the implementing process of DSMC method under thermodynamic non-equilibrium conditions. Statistic error about this method is investigated by comparing blunt cone aerodynamics under different boundary conditions. The results show that this method is available for estimating adiabatic wall temperature. Statistic error of heat transfer rate decreases rapidly with the increase of sampling steps, and ultimately it is within 0.5%.

关 键 词：稀薄气体 热非平衡 直接模拟蒙特卡罗仿真 绝热边界 误差分析 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]