摘要
通过求解N-S方程,对某空空导弹燃气舵在不同状况下的三维湍流干扰流场进行数值仿真,得到了燃气舵在不同舵偏角下绕流流场的复杂波系结构,计算了测量舵在无干扰舵和有干扰舵情况下升力和阻力等参量随舵偏角的变化曲线。所得舵间干扰相对误差不超过2%,与实际要求相吻合。结果表明,所采用的流动模型和数值模拟方法对燃气舵的气动性能进行预示是有效的。
3D turbulent interference flow field of some air-air missile under different conditions was numerically simulated by solving N-S equation, then complex wave structure of flow field of gas vanes under different vane deflection angles was obtained. The change curve of lift and drag with deflection angle with or without interference vanes was given. The relative error of the vane interference was less than 2 % ,which meets actual requirements. The results show that the flow model and numerical simulation can effectively predict aerodynamic performance of gas vane.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2008年第2期141-144,共4页
Journal of Solid Rocket Technology
关键词
舵偏角
数值仿真
燃气舵
舵间干扰
升力
阻力
deflection angle
numerical simulation
gas vane
vane interference
lift
drag
