摘要
针对NASA TrapWing高升力全展襟翼构型,采用计算流体力学(CFD)方法进行三维复杂流场仿真模拟,考察网格尺度和湍流模型对高升力模型气动特性的影响。采用"超立方体"概念,生成绕Trap Wing模型的不同网格密度高质量多块结构网格,通过求解雷诺平均Navier-Stokes方程,研究网格尺度对高升力模型气动特性的影响。在此基础上选取中等规模计算网格,考察Spalart Allmaras和Menter k-ωSST湍流模型对高升力全展构型流场模拟能力,分析湍流模型对气动特性的影响。研究结果表明:网格策略具有较好的网格收敛性;湍流模型对翼稍附近位置上翼面压力系数的预测稍有影响,SA湍流模型预测的压力系数较SST更接近实验值。确认研究工作为大型飞机增升装置数值模拟提供了一定的参考。
The article studies NASA Trap Wing with full- span configuration using CFD methods,in order to research the effect of grid density and turbulence models on the aerodynamic characteristics. To start with,Tesseract hypercube conception is used to generate high quality multi- block patching grid. Then the influence of grid density on the aerodynamic characteristics of NASA Trap Wing is studied. On this basis,the influence of Spalart Allmaras model and Menter k- ω SST model on the aerodynamic characteristics is analyzed with medium grid. The results show that such grid strategy can take on reasonable grid convergence. The turbulence models exert some effects on the pressure distribution especially on the position of wingtip. The Spalart Allmaras model achieves the higher accuracy than the Menter k- ω SST model. This study provides a valid numerical simulation method for the validation research of airplane high lift device.
出处
《航空计算技术》
2015年第1期84-86,90,共4页
Aeronautical Computing Technique
