空心弹空气阻力特性计算与数值仿真

应用Fluent软件仿真空心弹典型设计方案简化模型的空气动力流场，得到了其阻力系数与马赫数的关系，运用Matlab软件数值求解空心弹外弹道质心运动微分方程组，得到了弹道顶点和落点诸元。将以上所得阻力系数和弹道诸元与公式计算结果进行对比表明：在来流马赫数为2.0~4.4时，无弹带结构的简化空心弹模型用两种方法所得外弹道诸元结果相差很小；弹丸头部前缘厚度在可信区间内对阻力系数影响较小，但弹带结构对阻力系数的影响较大；工程设计时，受弹带结构影响，某空心弹简化模型阻力系数计算公式不太适合于工程问题求解，此时应以数值仿真为佳。

Theoretical Calculations and Numerical Simulation on Air Resistance Characteristics of Hollow Projectile

Simplified model hollow projectiles with typical design scheme was numerically simulated by Fluent software. The relationship between drag coefficient and Mach number was got. On this basis, trajectory centroid group equations of motion were solved using Matlab software,and the firing data of trajectory vertex and impact point was obtained. Compared the simulation results of drag coefficient above and ballistic firing data with theoretical formula calculation results,its shows that the results of simplified model hollow projectiles between simulation and theoretical calculations has a little difference when incoming flow Mach number between 2 . 0 and 4 . 4 . Leading edge thickness of hollow projectile has little effect on the drag coefficient in the confidence interval,but rotating band structure has a greater impact on the drag coefficient. Be effected by rotating band structure,the drag coefficient theoretical formula of simplified model hollow projectile is not suitable for solving engineering problem. Engineering design should be based numerical simulation.