超声速进气道整流罩船尾形状及其底阻的数值研究  

Stern Shape Design and Numerical Study of Base Drag for Supersonic Inlet Fairing

作　　者：徐悠悠[1] 谷良贤[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《弹箭与制导学报》2005年第S3期178-179,共2页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对超声速导弹进气道整流罩的底阻问题,文中采用CFD数值技术,模拟计算了某整流罩底部抛物形船尾附近绕流流场的压力分布,并由此得出船尾长度与整流罩高度之比对整流罩底部阻力大小的影响关系曲线,可为设计出低阻力的进气道整流罩提供参考。Adopted a numerical technique to deal with base drag of supersonic inlet fairing.Through CFD numerical analysis,simulated calculated the pressure distributing of flow field near the parabola stern of a fairing,and got the graph expressing the relationship between base drag and the ratio between stern length and fairing height.This result can be the reference to design a low base drag inlet fairing.

关 键 词：超声速进气道 整流罩 CFD 船尾 底阻 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程]