摘要
基于ANSYS 11.0的计算流体力学模块CFX,选取Reynolds平均的三维N-S方程及SST涡粘湍流模型,采用数值计算和流场可视化分析方法,对变前掠翼布局在低速起飞/着陆及高跨音速作战使用状态的气动性能进行了计算。着重对前掠翼与平直翼布局气动特性和流动机理进行了比较,通过对涡结构的分析发现,机翼前掠使得机翼前缘涡和鸭翼机身涡呈"V"字型靠近并相互加强,从而诱导出了二次涡,大大提高了对翼面气流分离的控制能力,验证了增大升力系数和失速迎角的机理。计算结果表明变前掠翼布局设计合理。
Based on the computational fluid dynamics module CFX of ANSYS 11.0, RANS 3 - D Navier - Stokes equation and SST model are selected. And the numerical method of N - S equation and visual flow - field simulation analysis are used to calculate the aerodynamic characteristics and flow mechanism of the configuration with variable forward swept and orthogonal wing in the stage of low speed taking - off/landing together with high transonic combat utilization. The comparison of the two configurations above shown that the wing 1 the secondary vortex eading is emphasized. The analysis of vortex configuration has edge vortex and canard vortex get closer and are is induced which greatly raises the control ability of the enhanced each other in V＇shape, thus flow seoaration uoon the winz. so thelift coefficient and stall angle are increased. The numerical results and analysis have proved the rationality of the guiding ideology and can provide theoretical supports to the advanced nature of the aircraft design with the configuration of variable swept wing.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2011年第4期1-4,共4页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国防预研基金资助项目(090251313058)
关键词
变前掠翼
气动特性
流动机理
数值分析
涡结构
气流分离
variable forward swept wing
aerodynamic characteristics
flow mechanism
vortex configuration
flowseparation
numerical analysis
