摘要
应用FLUENT软件对导弹发动机的尾焰流场进行数值模拟。计算得到了尾焰流场的温度云图、轴向温度曲线以及径向温度曲线,并分析了飞行条件对尾焰流场的影响。结果表明,尾焰进入空气后会发生复燃,产生高温区,距离喷管出口的位置越远,径向高温区的半径越大;随着飞行高度的增加,流场的复燃程度降低,但高温区的轴向和径向半径逐渐变大;随着飞行速度的变大,流场的复燃程度降低,高温区的轴向和径向半径逐渐变小。研究结果可为导弹的目标识别或防护奠定基础。
FLUENT software is applied to simulate the flow field of the tail flame of missile motor. Tempera-ture nephogram,the axial temperature curve and the radial temperature curve is obtained. On the basis of them the influence of flying conditions to the tail flame flow field are analyzed. The results show that,aftercombustion happens when the tail flame runs into the air,and generates high temperature area,with the increase of distance from the location of the nozzle exit,the radius of radial high temperature area becomes more bigger; with the increase of height,degree of after combustion is reduced,but the radiuses of axial and radial high temperature area becomes more bigger; with the increase of Mach number of flow,degree of aftercombustion is reduced,and the radiuses of axial and radial high temperature area becomes more smaller. The study provides the basis for the target recognition or protection of Missile.
出处
《战术导弹技术》
北大核心
2016年第4期75-81,共7页
Tactical Missile Technology
