导弹腹部进气道前弹体干扰特性数值分析  

Numerical analysis of missile forebody-ventral inlet interference characteristics

作　　者：徐东来[1] 陈凤明[1] 蔡飞超[1] 杨茂[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2010年第3期247-251,共5页Journal of Solid Rocket Technology

基　　金：总装创新项目(7130918)

摘　　要：为评价腹部进气中等超声速战术导弹中导弹前弹体干扰对进气道总体性能的影响,结合设计实例,基于F luent软件,运用CFD数值模拟技术,开展了进气道与导弹前弹身组合体内外流场的一体化数值仿真计算分析。结果表明,相比单独进气道,因导弹头部弓形激波造成的总压损失及前弹体附面层干扰两方面作用,腹部进气道的实际捕获流量和总压水平总体下降,平均下降幅度在设计点单一随攻角变化时分别达3.5%和3%,在低速飞行段单一随飞行速度变化时分别达3%和4%。此外,也证实导弹前弹体的屏蔽和预压缩作用可适度改善腹部进气道攻角特性,采用附面层隔道可弱化前弹体附面层干扰。In order to assess influence of forebody on overall inlet performance for medium supersonic tactical missiles with ventral inlet,CFD tool,FLUENT,was used to carry out numerical simulation of integrated internal and external flow fields of combined body-inlet.Results show that because of total pressure loss due to nose bow shock and forebody boundary layer interference,both captured flow and total pressure level of ventral inlet are lower than isolated inlet.Average reductions of 3.5% and 3%,respectively,are observed at design point with respect to angle of attack.And reductions of 3% and 4%,respectively,at low Mach number are also observed.In addition,forebody shielding and pre-compression effects can moderately improve inlet performance with respect to angle of attack,and boundary layer diverter can reduce forebody interference influences.

关 键 词：腹部进气道 超声速进气道 前弹体干扰 数值模拟 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程] V438[航空宇航科学与技术—航空宇航推进理论与工程]