进气道整流罩保形减阻设计研究  

Study on conformal and drag reduction design of inlet cowl

作　　者：李泽勇[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2008年第2期138-140,144,共4页Journal of Solid Rocket Technology

摘　　要：提出了一种尾喷管与进气道整流罩保形设计方案,既保持导弹外形特征不变,又与尾喷管内型面实现一体化保形设计。采用CFD方法对尾喷管及整流罩底部内外流场进行了一体化数值模拟,分析了保形设计对进气道整流罩底阻的影响。结果表明,导弹高速飞行时,采用保形设计能减小进气道整流罩的底阻;补燃室压强越高,进气道整流罩底阻越小,从而验证了该设计方案的可行性。A kind of conformal design scheme for tailpipe nozzle and inlet cowl was put forward, which not only keeps missile shape, but also realizes integral conformal design with inner contour of nozzle. The internal and external flow field at the bottom of tailpipe nozzle and inlet cowl was numerically simulated by means of CFD methods, and the effects of conformal design on drag of inlet cowl were analyzed. The results show that conformal design reduces base drag of inlet cowl during high-speed flight; the higher the chamber pressure is, the smaller base drag of inlet cowl is. It is proven.that the scheme is feasible.

关 键 词：进气道 保形设计 底阻 计算流体动力学 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]