混合网格方法在栅格翼数值模拟中的应用研究

栅格翼是采用一种蜂房结构设计的升力面和控制面,和传统舵面相比具有铰链力矩小、能在较大攻角下保持升力等特点,并得到了越来越广泛的应用。由于栅格尾翼的特殊结构,网格生成具有很大的难度。本文采用了结构、非结构混合网格的办法,在弹体和栅格翼的物面附近区域,生成适合粘性计算的大长宽比的结构网格,弹体网格和栅格翼网格之间采用非结构网格进行填充,满足非结构网格和结构网格交接面的完全对接。本文基于结构/非结构网格体系采用有限体积方法求解NS方程,对不同舵偏角下的栅格翼构形进行了数值模拟,并通过实验结果对数值方法进行了验证。

Flow simulation of missile with grid fins using structured-unstructured hybrid grids

A grid fin is an unconventional aerodynamic lifting device consisting of an outer frame with internal grid framework.The unique structural characteristics of the grid fin can provide high lift and result in near zero hinge moments.Usually CFD can be used to predict the aerodynamic force of missiles with grid fins,but when the fin turns around its axis,the building up of the grid becomes too complicated to make.In this paper,the structured-unstructured hybrid grids was applied to the simulation,which consist of structured grids around the body and grid fins and unstructured grids filling the gap between different structured grid blocks,and the faces between structured grids and unstructured grids are common.Based on the hybrid grid structure,the Navier-Stokes equations were resolved with finite volume method to simulate the supersonic flow field of model missile with grid fins,two fin deflection angle were involved,experimental data was applied to validate the method.