摘要
采用数值模拟方法,研究了高度H=0-35 km,Ma=0-4范围的助推器尾喷流对底部阻力的影响作用,获得了有、无尾喷流情况下底部阻力数据的变化规律。研究结果表明,在不同的高度、来流马赫数下,尾喷流对底阻的影响程度不同。与无喷状态的底阻相比,在低空、亚声速状态,尾喷流的抽吸引射效应较强,导致底部压力降低,底阻系数增大;在高空、超声速状态,外界大气压降低,尾喷流的膨胀角增大,导致底部压力增大,底阻系数降低;随着飞行高度进一步增大,外界大气压进一步降低,尾喷流充分膨胀,助推器尾喷流和外表面绕流干涉形成斜激波,助推器底部压力进一步增大,甚至形成附加推力。
The effects on base drag change causing by jet of booster in the conditions of 0 - 35 km are studied numerically, and Mach number of 0 - 4 and change laws of base drag in both conditions with or without jet are acquired. The results show that the effect degree of base drag causing by booster jet is changing with the changes of altitude and Mach number. Compared with the condition of without jet, the base pressure reduces and base drag raises because of the ejector action causing by booster jet in the conditions of low altitude and subsonic, under high altitude and supersonic conditions, base drag reduces be-cause of environment pressure reduces and expansion angle raises leading to base pressure reduces. With the altitude increasing and environment pressure decreasing, the booster jet and extern flow produce an interference pattern and form shock waves, which lead to the increase of base pressure, even produce additive thrust.
出处
《战术导弹技术》
北大核心
2016年第6期33-37,50,共6页
Tactical Missile Technology
关键词
喷流
底部阻力
边界层
分离涡
剪切层
激波
膨胀波
jet
bottom drag
boundary layer
separated vortex
shear layer
shock wave
expansion wave
