利用数值模拟的方法对单兵火箭弹的主要空气动力系数进行求解,运用流体动力学Fluent软件对单兵火箭弹的空气特性进行数值仿真,求解出火箭弹在攻角a=0~15°范围内的升力系数和阻力系数值。将数值计算结果与试验数据进行对比,结果表明,升力系数随攻角增大而递增;阻力系数在攻角a=2°时最小,之后随攻角递增,并且随攻角变化曲线与试验结果相近。

The numerical simulation was used to solve the main aerodynamic coefficients of the individual rocket weapon; the CFD method was applied to study the aerodynamic characteristics of the individual rocket weapon. When the angle of attack is 0°~15°, some aerodynamic characteristic values were solved, including the lift coefficient and the drag coefficient. By comparing the computing results with the experimental results, it shows that the lift increases with the increase of the angle of attack. The drag coefficient is minimum when a = 2°, then increasing with the angle of attack, the curve is almost the same with experiment result.