操纵面偏转绕流数值研究  

Numerical investigation of control surfaces deflection

作　　者：黎军[1] 张宇飞[2] 李天[1] 陈海昕[2] 

机构地区：[1]北京航空航天大学,北京100083 [2]清华大学航天航空学院,北京100084

出　　处：《空气动力学学报》2008年第3期384-387,共4页Acta Aerodynamica Sinica

摘　　要：针对飞机操纵面偏转绕流计算的困难,本文介绍了一种窗口嵌入和面搭接的多块网格技术对飞机操纵面进行分解处理,在基本构型网格下嵌入偏转网格替代原有网格,选用Roe格式、LU-SGS时间推进方法和k-g湍流模式开展数值计算,计算结果与实验结果得到了很好的吻合。To dispose of the difficulty of numerical simulation about flow around control surfaces deflection, The Window Embedment grid technology and the surface patch method of multi-block structural grid are used to decompose an aircraft configuration with control surfaces into several parts and generate grid blocks separately. The grid blocks of control surfaces are embedded into the grid of the baseline configuration to replace the original grids. Roe＇ s Flux Difference Splitting （FDS） scheme,the fully implicit lower-upper symmetric-Gauss-Seidel （LU-SGS） temporal differentiation and k-g turbulence model are employed for the computation. The numerical results match well with experimental data.

关 键 词：操纵面 窗口嵌入 多块网格 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]