摘要
文章在多块结构化框架下,采用面积加权平均的方法进行通量守恒传递,并成功地应用于存在"剪刀差"的全机增升装置复杂外形绕流N-S方程数值分析。通过对某民机全机低速构形所进行的气动力数值分析,计算结果与风洞实验结果吻合良好,表明该方法可以比较好地模拟如此复杂外形的流动细节,从而验证了文中所采用的面搭接多重网格技术、网格生成策略及流场计算方法的有效性。
Aim. The introduction of the full paper points out the urgent need for and the great difficulties involved in searching for the feasible method of CFD（ computational fluid dynamics） simulation mentioned in the above rifle. We believe that our explorative efforts have resulted in a step forward. Section 1 briefs the usual method for the grid generation of 3D complex aircraft configuration. Section 2 uses the patched-grid technique, the third-order upwind- biased implicit flux-difference splitting （FDS） method and the implicit approximate factor decomposition method to discretize and solve the Navier-Stokes （N-S） equations. Section 3 uses the mulri-grid technique to accelerate the convergence of the N-S equations. Section 4 presents and analyzes the calculation results in Figs. 6 and 7 ; the aerodynamic numerical analysis of the landing configuration and takeoff configuration of a certain aircraft with low Reynolds number shows preliminarily that our simulation method is indeed feasible for simulating the flow of very complex aircraft configuration.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2010年第1期143-146,共4页
Journal of Northwestern Polytechnical University
基金
国家自然科学基金(10772148)资助
关键词
面搭接多重网格技术
N-S方程
全机增升装置构形
computational fluid dynamics, aircraft, Naver-Stokes equations, patched grid, multi-grid technique, high-lift aircraft configuration
