多片尾翼布局弹箭气动特性数值计算  

Numerical Investigation of Aerodynamic Characteristics for Multi-Fin Rockets/Missiles

作　　者：雷娟棉 居贤铭[1] 苗瑞生[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《北京理工大学学报》2003年第6期686-689,共4页Transactions of Beijing Institute of Technology

基　　金：国家部委预研项目(4013130305)

摘　　要：用数值模拟方法研究多片尾翼布局弹箭的气动特性.以三维Navier-Stokes方程为控制方程,用CFD方法对4片、6片与8片平直形尾翼和卷弧形尾翼弹箭的流场进行数值模拟研究,得到的气动特性结果与风洞实验结果基本吻合,为多片尾翼布局弹箭的气动设计及尾翼片数的合理选择提供了依据.Computational fluid dynamics (CFD) numerical simulation is used in the investigation of aerodynamic characteristics of multi-fin rockets/missiles. Three-dimensional Navier-Stokes equations are used as the control equations. Flow fields of rockets/missiles with four, six and eight straight or wrap around fins are simulated with the CFD numerical method. Computational aerodynamic characteristics are found to be in good agreement with wind tunnel test results, thus it can be taken as a foundation in multi-fin rockets/missiles aerodynamic design and in the choice of fin numbers.

关 键 词：多片尾翼布局弹箭 气动外形 气动特性 数值模拟 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]