导弹减阻杆减阻的数值仿真研究

Numerical Simulation Study on Missile Antidrag Spike Drag Reduction

为了解决导弹有效载荷和射程之间的矛盾,减小导弹阻力是个有效途径。通过在导弹头部安装减阻杆装置来达到设计目的,从理论上分析了在超音速飞行时导弹减阻杆的流场特征,给出了导弹减阻杆减阻机理,并借助CFD计算软件FLUENT,通过求解雷诺平均Navier-Stokes方程组,采用Roe-FDS格式对方程进行空间离散,并选用标准k-ε湍流模型,对导弹减阻杆流场进行数值仿真。仿真结果显示,减阻杆能够改变导弹头部流场形态,显著减小导弹头部阻力。同时文中对比了美国ISL实验室的部分风洞实验数据,对比结果显示数值仿真结果良好,减阻杆装置可以达到设计目的。

Drag reduction is an effective way to increase the payload and the range of the missile. By installing a spike on the nose of the missile, drag reduction can be achieved. And the mechanism was analyzed theoretically as the flow field of the spike was characterized. To get more precise result, CFD work was setup then. The Navier Stokes equation was Spatial Diseretized applying the Roe FDS format and the standard k e turbulence model, and then the N S equation can be solved. The numerical result reveals that the nose flow field is changed notably by the spike and the drag of the missile is reduced at certain amounts. The wind tunnel test data of the ISL lab are compared with this computation and show good consistency.