基于结构网格的栅格翼绕流数值模拟

Numerical simulation of a grid fin missile based on structure grid

针对栅格翼这种复杂的构造形式,采取有效的多块结构网格生成策略,对栅格翼导弹生成高质量贴体的结构网格。在此基础上,通过求解N-S方程,对栅格翼导弹亚、跨、超声速绕流流场进行了数值模拟。计算结果与风洞试验结果吻合较好,能够准确地捕捉到栅格框内复杂流场的流动特性,从而结构网格生成策略与计算方法得到验证,为栅格翼导弹绕流流场的精确数值模拟提供了技术途径。

Grid fin,also known as lattice control,is a kind of unconventional aerodynamic lifting and control surfaces that consists of an outer frame supporting an inner grid of intersecting planar surfaces with small chord.In this paper an efficient meshing strategy is developed to generate high quality point-to-point multi-block structured grid for such a complex geometry.The N-S equations are solved numerically using the finite volume method on the herein generated multi-block structured grid,adopting multi-grid method to ac-celerate the convergence.With these strategies the flow around a grid-finned missile is simulated at subson-ic,transonic and supersonic states,with free stream Mach number ranging from 0.5 to 3.The simulation results show excellent agreement with the experiment data for the aerodynamic forces and moments.Detailed flow field is also obtained that exhibits the complex flow properties inside the grid frame.The results provide an effective means for accurate simulation of grid fin missiles flow fields.