摘要
采用计算流体力学(CFD)技术,对某型运载火箭动力系统试验时尾流辐射场进行了数值模拟。计算采用氢氧单步燃烧反应模型,标准k-ε湍流模型获得燃烧流场,同时利用P1辐射模型法考虑热辐射的影响,并引入灰气体加权模型确定气体介质的辐射特性。仿真结果同试验结果进行了对比分析,结果表明,箭体底部的换热方式以辐射换热为主,P1辐射模型可以有效地预测火箭发动机尾流辐射场。
Numerical investigations of a large launch vehicle stage test are conducted by CFD technique. The uni-step H-O reaction model, standard k-ε turbulence model, P1 radiation computation model and the weighted-sum-of-gray-gases model are employed to obtain the flow field. The simulation is evaluated by comparison with the experimental results. The results show that radiation plays magisterial role in heat transfer around the rocket bottom, and P1 radiation computation model can predict the tail radiation fields of the rocket engine effectively.
出处
《导弹与航天运载技术》
北大核心
2016年第4期67-71,共5页
Missiles and Space Vehicles
关键词
动力系统试验
仿真
辐射
P1辐射模型法
Launch vehicle stage test
Simulation
Radiation
P1 radiation computatiorl model
作者简介
罗天培（1987-），男，工程师，研究方向为火箭发动机试验技术
