摘要
采用二维雷诺平均N-S方程和RNGk-ε湍流模型,对某空空导弹发动机在高低空环境下的燃气射流流场进行了数值模拟,得到了发动机射流流场的马赫数等值线云图、射流流场大小,给出了射流轴线上的流动参数曲线,分析了燃烧室工作状态和飞行高度对发动机射流流场的影响。结果表明,在发动机排气质量流率相同的情况下,高空时燃气射流流场的边界比低空大;相同飞行高度时,随着发动机排气质量流率的增加,燃气射流流场边界随之增大,同时射流流场的结构也有很大的不同。数值模拟为该型号空空导弹发动机的气动布局提供了依据。
The complex flow-field of combust gas injection for SRM was numerically simulated by using two-dimensional average Reynolds equations and the K-ε turbulent model. The Mach number contour and flow-field area of combust gas injection flow-field of the air-to-air missile rocket motor was numerically simulated. The parameter curves on axis were given. The influences of different combustion chamber status and flight altitude were analyzed and investigated. The results show that the flow-field boundary augments with increase of fight altitude at the same flight Mach number and the same mass flow rate, and augments with the increase of mass flow rate at the same flight. At the same time, the combustion gas injection flow-field structures change greatly with the variety of flight status parameters. The numerical simulation results provide basis for the optimal design on the gasdynamic distribution of air to air missile.
出处
《系统仿真学报》
EI
CAS
CSCD
北大核心
2007年第16期3672-3675,共4页
Journal of System Simulation
关键词
固体火箭
发动机
流场
高低空
数值模拟
solid rocket
motor
flow field
high-low altitude
numerical simulation~ ]
