为研究十字形尾翼导弹模型的空气动力学的特性,通过三维建模软件对导弹模型三维实体化,并通过网格划分软件对三维模型进行网格划分,采用Fluent中湍流Spalart-Allmaras模型对导弹模型的气动特征进行分析。采用数值模拟的方法来研究空气绕流此导弹模型的流动情况,并分析导弹在不同马赫数和不同攻角时空气动力、力矩、阻力系数、升力系数变化规律。研究的结果对十字型尾翼导弹的气动动力设计及后续飞行控制系统的设计有重要的意义。

In order to study the aerodynamic characteristics of the cruciform tail missile model, the three-dimensional modeling of the missile is carried out by three-dimensional modeling software. The three-dimensional model is meshed by the grid partitioning software. The aerodynamic characteristics of the missile model are analyzed by using the Spalart-Allmaras turbulence mode. The numerical simulation is used to study the flow condition circumstance of air around the missile model, and the regular patterns of aerodynamics, moment, drag coefficient and lift coefficient of missiles in different Mach numbers and different angles of attack are analyzed. The results of the study are of great significance to the aerodynamic design of the missile with cross-shaped tail and the subsequent design of the flight control system.