针对尾翼结构对大长径比火箭弹外流场的影响，建立3 种翼型火箭弹的3 维简化模型。在保证3 种尾翼 都能折叠到弹径尺寸的前提下，对3 种翼型火箭弹进行数值模拟，分析对比不同尾翼结构尾翼火箭弹的气动特性差 异，并验证了文中所采用数值计算方法的可行性。结果表明：增加卷弧翼数量会使弹箭的阻力系数增加，并使俯仰 力矩系数增大，弹箭的稳定性提高；相同尾翼数量的卷弧翼比平板尾翼的升力系数高，飞行过程中卷弧翼能产生更 大的升力；平板尾翼的侧向力矩系数绝对值比卷弧翼低。
Aiming at the influence of the tail structure on the external flow field of the rocket with large aspect ratio, the three-dimensional simplified models of 3 kinds of aerofoil rockets were established. On the premise that the 3 kinds of tail can be folded to the diameter of the projectile, the three kinds of airfoil rockets are numerically simulated, and the aerodynamic characteristics of the rockets with different tail structures are analyzed and compared, and the feasibility of the numerical calculation method used in this paper is verified. The results show that increasing the number of wrap-around wings can increase the drag coefficient and the pitching moment coefficient of the projectile, and improve the stability of the projectile. The lift coefficient of wrap-around wings with the same number of wings is higher than that of flat wings, which can produce more lift during flight.The absolute value of lateral moment coefficient of flat wings is lower than that of wrap- around wings.