某型民机着陆构型粘性气动力计算  

Simulation of Viscous Flow For a Civil Aviation Aircraft in Landing Configuration

作　　者：廖振荣[1] 钱瑞战[1] 邓一菊[1] 

机构地区：[1]中航一集团第一飞机设计研究院总体气动设计研究所,陕西西安710089

出　　处：《航空计算技术》2008年第5期33-36,共4页Aeronautical Computing Technique

摘　　要：采用ICEM对某型民机着陆构型进行多块结构化点对点网格剖分,运用基于N-S方程的WISE MAN PLUS软件对该构型低速粘性复杂流场进行数值模拟。在进场条件下,计算的升力和试验值误差在3.8%以内,俯仰力矩和试验误差在3.6%以内;计算与试验失速迎角差别在1°左右,最大升力系数较试验小6.3%。同时还给出了一些流场显示结果,对复杂流场进行了机理分析。计算与风洞试验结果符合较好,满足工程需要。Multi- block structured point to point grids have been generated by ICEM for a civil aviation aircraft in landing configuration. The low speed viscous complex flow is simulated using the WISEMAN PLUS software,based on N- S equations. At approach condition,the difference between computed lift coefficient and experimental data is less than 3. 8% , the pitching moment is less than 3.6%. The stall angle is less than 1 degree, and the computed maximum lift coefficient is 6.3 % below the experiment. The paper also presents some insight research of the complex flow field. The results show that the CFD simulation fits well with the wind tunnel test and satisfies the engineering requirements.

关 键 词：N-S方程 着陆构型 多块结构网格 低速流场 

分 类 号：V212.11[航空宇航科学与技术—航空宇航推进理论与工程]