炮弹尾翼弦长对气动特性的影响

Influence of fin chord length on aerodynamic characteristics of a shell

为研究炮弹新型尾翼结构,其弦长对气动特性的影响。基于尾翼稳定的要求,利用计算流体力学(CFD)进行数值模拟,在验证数值方法的基础上,对不同尾翼弦长的炮弹流场进行了数值模拟,并对计算结果进行对比分析。结果表明:基于计算模型的可靠性,将尾翼弦长分为前、后弦长,在固定总弦长、增加后弦长时,阻力系数与升力系数均随之减小;在固定前弦长、增加后弦长时,具有减阻增升增稳作用。研究结果为不同结构限制下的弹体设计提供参考依据。

In order to study the influence of the chord length on the aerodynamic characteristics of a new tail structure of a shell,based on the requirements of the stability of the tail,computational fluid dynamics is used for numerical simulation.On the basis of verifying the numerical method,the flow field of a shell with different chord lengths of the tail is simulated numerically,and the calculated results are compared and analyzed.The results show that:based on the reliability of the calculation model,the tail chord length is divided into front and rear chord lengths.When the total chord length is fixed,the increase of rear chord length has drag reduction effect,while the increase of front chord length has drag reduction effect and lift effect.The results can provide reference for the design of missile body under different structural constraints.