矩形截面弹身—尾翼组合气动特性的数值计算  

Numerical Computing for the Aerodynamic Characteristics of Rectangular Cross-sectional Body—Tail Configurations

作　　者：耿永兵[1] 居贤铭[1] 黄晓鹏[1] 

机构地区：[1]北京理工大学,北京100081

出　　处：《弹箭与制导学报》2002年第S1期164-167,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中对矩形截面弹身—尾翼组合体的亚音速气动特性进行了数值计算,计算条件为 M=0.4～0.9,α=0°～10°,给出气功特性曲线,并与风洞试验结果进行了比较。In this paper,the subsonic aerodynamics of rectangular cross-sectional boby-tail configurations is researched by numerical simulation.The condition of computation is M=0.4～0.9 and α=0°～10°.The aerodynamic parameters is obtained,and compared with experimental data..

关 键 词：非圆截面导弹 数值模拟 气动特性 

分 类 号：E911[军事]