摘要
采用C-H型混合的结构化网格,选用W ilcox提出的k-ω模型求解可压的N-S方程,模拟了多段翼型的流场。结果表明:在4°和6°迎角下的非定常计算结果与试验结果的对比,计算结果与试验值吻合的较好。本文应用了亚迭代时间法,正确地描述了30P30N多段翼型前缘结构区域的流动特征和流动机理。
To simulate the flow around the multi-element airfoil, we have undertaken a computational study through solve the N-S equation with C and H hybrid structure grid. The k-ω turbulence model which Wilcox advanced is adopted for the numerical simulation. The present paper presents the accompanying computational results including a comparison between computation and experiment at 4 and 6 degree angles of attack, and the unsteady results which we have computed agree well with the measured data.. In this paper the subiterations method is adopted, and this numerical method can availability simulate the flow character and mechanism near leading-edge slat.
出处
《飞机设计》
2008年第2期6-10,共5页
Aircraft Design
基金
航空基础科学基金资助项目(2006ZB51023)
关键词
多段翼
k-ω两方程模型
非定常流
亚迭代步
multi-element airfoil
k-ω two equations turbulence model
unsteady flow
subiterations
