三维高超声速稀薄气体流场通量分裂式DSMC-IP方法研究  

RESEARCH ON A FLUX-SPLITTING METHOD IN THREE DIMENSIONAL HYPERSONIC RAREFIED FLOW FIELD

作　　者：许啸[1] 王学德[1] 谭俊杰[1] 

机构地区：[1]南京理工大学能源与动力工程学院,南京210094

出　　处：《工程力学》2016年第8期238-247,共10页Engineering Mechanics

基　　金：总装备部预研基金项目(9140A13020913BQ02183);南京理工大学紫金之星计划项目;江苏省青蓝工程项目

摘　　要：结合非结构网格对复杂外形精确描述的能力和IP(Information Preservation)方法降低统计耗散的特点,该文在非结构网格的基础上构建了改进型通量分裂式DSMC(Direct Simulation of Monte Carlo)-IP数值方法,对三维高超声速稀薄气体流场进行了数值模拟。采用渐变尺度的非结构网格划分流场区域,在满足DSMC方法对网格尺度需求的同时,对流场的结构特点进行精确描述;另外根据Van Leer格式的思想改进IP方法中的通量计算格式,解决了激波处的数值间断问题;并采用单元信息保存法对IP方法进行补充,提高了计算方法的稳定性。通过对三维圆球绕流和航天飞机头部绕流流场的数值模拟,验证了该文方法的有效性和可行性,并对模型中的气动特性和参数分布规律进行了分析。The paper presents an improved DSMC（Direct Simulation of Monte Carlo）-IP method that has been combined with unstructured grid and IP（Information Preservation） method, and uses the method to simulate a three dimensional hypersonic rarefied flow field. The gradient scale unstructured grid is used to meet the DSMC computational requirement and describing the characteristics of the flow field; the flux computational format in IP method is improved using the Van Leer format to solve the numerical discontinuity problem in the shock region; the cell information preservation method is proposed to improve the stability of the IP method. The feasibility and effectiveness of the improved DSMC-IP method is validated by the simulation results of flow across a sphere and the head of a space vehicle, and the aerodynamic characteristics and regularity of parameter distribution are analyzed.

关 键 词：临近空间 高超声速 稀薄气体 DSMC-IP方法 三维非结构网格 

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]