COMPUTATION OF DYNAMIC STALL OF A NACA-0012 AIRFOIL

被引：21

作者：

SHIDA, Y

KUWAHARA, K

ONO, K

TAKAMI, H

机构：

[1] INST SPACE & ASTRONAUT SCI,TOKYO 153,JAPAN

[2] NIHON UNIV,COLL SCI & TECHNOL,TOKYO 101,JAPAN

来源：

AIAA JOURNAL | 1987年 / 25卷 / 03期

关键词：

FLOW OF FLUIDS - MATHEMATICAL TECHNIQUES - Finite Difference Method;

D O I：

10.2514/3.9638

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The flowfield around a NACA-0012 airfoil oscillating in pitch about a 0. 25 chord is analyzed by solving the two-dimensional compressible Navier-Stokes equations. A block pentadiagonal matrix scheme based on the approximate factorization method is adopted. Two meshes, 161 multiplied by 40 and 321 multiplied by 80, are used. In the case of the coarse mesh, lift stall is captured. In the case of the fine mesh, not only lift stall but also the restoration process of the lift coefficient on the downstroke is captured.

引用

页码：408 / 413

页数：6