为了研究攻角对某坦克炮超口径垂直尾翼稳定弹丸气动特性的影响,给引信弹道环境分析提供参考,应用FLUENT软件,对某大口径坦克炮超口径垂直尾翼稳定弹丸的简化模型进行三维数值模拟,得到该弹丸各气动特性参数。二次函数C_D=C₀(1+Kα²)可用来描述弹丸阻力系数C_D随攻角的变化,攻角系数K取值范围为13.0~16.8。在亚音速段和跨音速段,三次函数更适合用来描述升力系数C_L和俯仰力矩系数C_mz随攻角的变化,而在超音速段,一次函数和三次函数都适合。

In order to study the influence of attack angle on aerodynamic characteristics of a super caliber fin stabilized projectile of tank gun, providing refereces for analysis of ballistic condition of fuze, the aerodynamic characteristic parameters of the projectile were got by FLUENT. The analysis shows that quadratic function can be used to describe the drag coefficient C_D of projectile varying with attack angle and the attack angle coefficient is 13.0~16.8. In subsonic and transonic region, the cubic function is more suitable to describe the lift coefficient C_L and the pitching moment coefficient C_mz of the projectile varying with attack angle. In supersonic region, linear function and cubic function are both appropriate.