翼－身－尾组合体绕流的Euler方程计算  

Computation of the Flow past Wing-Body-Tail Combinations Using Euler Equations

作　　者：黄明恪[1] 陈红全[1] 成娟[1] 

机构地区：[1]南京航空航天大学

出　　处：《空气动力学学报》1995年第3期349-354,共6页Acta Aerodynamica Sinica

摘　　要：本文采用重迭网格技术和ＥＪｅｒ方程计算翼－身－尾组合体绕流。对算身与尾。身部分采用各自的Ｈ。Ｏ型网格，Ｅ＊ｅ／方程求解采用１ａｍｅｓｏｎ的有限体积法，即中心差分近似和显式Ｒｕｎｇｅ·Ｋｕｔｔａ时间推进。采用前后区交替迭代使前后两区通过重迭区交换信息。本文用ＮＡＣＡＴＮ４０４１翼－身，尾模型为例，计算的空气动力特性与实验符合较好。The Euler equations and the overlap grid technique areapplied to compute the flow past wing-body-tail combinations.The so-lution of the Euler equations uses the finite volume method,the centraldifference scheme with a blending of 2nd and 4th difference dissipation termsand Runge-Kutta explicit multistage scheme. The computation is perform-ed alternately on forward region around the wing-body and on rear regionaround the tail-body,with the use of different H-O grids in two regions.The flows in two regions are coupled with each other by the informationtransferred through the overlap region. The computation of the flow pastan airplane model given in NACA TN 4041 is performed with the presentmethod at Mach number of 0.8.It is shown that the computed aerodynamiccharacteristics are in good agreement with the experiment results for an-gles of attack up to 16°.

关 键 词：欧拉方程 有限体积法 翼身尾组合体 机翼 

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]