非结构网格上N-S方程解法研究及在多段翼型绕流中的应用  

Computation of the flow past multi-element airfoils using unstructured grid and N-S equations

作　　者：刘学强[1] 伍贻兆[1] 

机构地区：[1]南京航空航天大学空气动力学系,江苏南京210016

出　　处：《空气动力学学报》2001年第2期223-227,共5页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目! (19982 0 0 9)

摘　　要：在非结构网格上求解N S方程时 ,靠近物面的网格伸展比相当大 ,用有限体积法进行显式求解时不易收敛并且对雷诺数有一定的限制。本文采用的人工耗散项中含有网格的方向尺度 ,因而在不同区域选取不同 :在粘性区内该项比物理粘性项小得多 ,在粘性区外与Jameson的人工耗散项相同。生成非结构网格采用的是层推进技术与传统的阵面推进法相结合的方法 ,这样能保证在粘性区内网格有一定的方向规则 。When we solute the Navier Stokes equations on unstructured triangular meshes, the meshes which are near to the wall have high aspect ratio, using the finite volume approximation'method the integration to steady state is difficult to achieve. In this paper, directional scaling of the artificial dissipation is achieved by considering local mesh stretching vectors at each point, so the artificial dissipation is difference according to the field of computation. The method of generating unstructured triangular grids with some having high aspect ratio is based on a grid marching strategy referred to as advancing layers forconstruction of highly stretched cells in the boundary layer and the conventional advancing front technique for generation of regular, equilateral cells in the inviscid flow region.

关 键 词：非结构网格 N-S方程 多段翼型 翼型绕流 机翼 飞机 空气动力学 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]