摘要
为了给长尾喷管热防护结构的烧蚀和温度场计算提供准确的热边界条件,从二维轴对称N S方程出发,采用颗粒轨道模型和有限体积的Jameson格式计算了长尾喷管纯气相流场和两相流流场。分析和比较表明:在长尾喷管喉部附近以及扩散段的相同轴向位置,两相流情况下轴线上的燃气马赫数小于纯气相情况下的马赫数,两相流情况下轴线和壁面上的燃气温度大于纯气相情况下的燃气温度;在进行长尾喷管热防护结构设计时应以两相流流场作为热边界条件。
To provide thermal boundaries for the calculation of ablation and temperature fields of the heatresistant construction,particletrajectory model and Jameson scheme of finite volume method were used to simulate the onephase and twophase flow fields for a tailpipe nozzle. The numerical results show that the gas Mach number for twophase is lower than those for onephase at the centerline,the gas temperature for twophase is higher than those for onephase at both the centerline and the wall around the throat and expansion segment, twophase flow should be considered into the design of the heatresistant construction.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2002年第5期425-427,共3页
Journal of Propulsion Technology
关键词
长尾喷管
喷管气流
二相流
流动分布
数值仿真
Tailpipe nozzle
Nozzle flow
Two phase flow
Flow distribution
Numerical simulation
