旋转弹丸空气动力特性数值解法

为提高在弹道计算和弹丸设计中弹丸空气动力系数精度,采用隐式LU算法求解N S方程并考虑代数湍流模型,在旋转物面边界条件下计算弹丸的阻力、升力、俯仰力矩、滚转阻尼力矩、马格努斯力和力矩。通过对美国T388等弹丸的气动力系数计算并与弹道靶试验数据进行比较,以及对某榴弹的气动力计算结果在弹道计算中进行应用分析,表明用数值模拟得到的旋转弹丸空气动力系数好于以前用工程方法给出的结果。

Numerical Solution of the Aerodynamic Properties of the Rotating Projectiles

To improve the precision of the aerodynamic coefficients of the projectiles during calculating trajectories and designing projectiles, the drag, lift, pitching moment, roll damping moment, Magnus force and moment of the projectiles are computed by solving N-S equations applying an implicit LU scheme, and considering an algebraic turbulence model and the boundary condition for rotating body surface. It is indicated that the aerodynamic coefficients of the rotating projectiles obtained by means of the numerical simulation are better than those previously obtained by means of the engineering estimate by the comparison of the computing results and the experimental results of the T388 shell, and by the ballistic calculations of a certain howitzer projectile using the aerodynamic coefficients obtained with this technique.