为了某亚音速末修火箭弹弹道修正设计和分析提供参考,应用空气动力学理论推导了弹丸阻力系数与攻角和弹丸形状参数的关系式,并用FLUENT软件仿真得到该火箭弹在攻角0°~14°、马赫数0.2~0.9、阻尼翼张开与否条件下阻力系数。仿真结果表明所得理论公式用于该亚音速末修火箭弹非零攻角下阻力系数估计时,相对误差绝对值最大是16.56%,相对误差绝对值的平均值最大是9.97%,可用于弹药工程设计.

In order to provide reference for trajectory correction design and analysis of a subsonic rocket with terminal trajectory correction, the function of relationship among a projectile drag coefficient, attack angle and figure was deduced by using the theory of aerodynamics. The rocket's drag coefficients were obtained by using FLUENT software under some conditions, which including attack angle 0° ~ 14°, Mach number 0.2~0.9 and damping vane opening or not. The simulation results show that the maximum absolute value of relative error is 16.56%, the maximum value of average absolute value of relative error when the equation deduced is used to expect drag coefficient of non-zero attack angle on this subsonic rocket with terminal trajectory correction.