基于工程和数值方法的导弹气动特性计算

Calculation of Missile Aerodynamic Characteristics Based on Engineering and Numerical Methods

导弹气动特性对导弹设计及使用具有重大意义,气动特性的确定是弹道计算、控制参数的选择和结构强度设计的原始依据,其优劣直接影响导弹的飞行性能。针对某型导弹风洞模型,采用一般工程计算方法及FLUENT软件,分别从工程与数值两个方面对其在亚声速条件下的气动特性进行研究,然后将计算所得的主要气动力系数与风洞实验结果进行对比,从而对不同计算方法的精度进行评价。结果表明,二者所计算的气动参数在一定范围内满足工程设计的精度要求,能较为准确地反映导弹的气动特性。

During the missile design process, the determination of missile aerodynamic characteristics is the original reference of the trajectory calculation, the selection of control parameters, the design of structural strength, and the aerodynamic characteristics determines the flight performance of a missile. In this paper, a certain type of missile model is given at first, then engineering estimation and FLUENT software are adopted to study its subsonic aerodynamic characteristics separately from the engineering estimation and numerical simulation. The accuracy of different experimentation method is verified basedon the comparison between the calculated parameters and the wind tunnel experimental results. The results show that the aerodynamics parameters calculated from the both can meet the real requirements of engineering design,and also can reflect the missile＇s aerodynamic characteristics accurately.