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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。
According to the NASA TrapWing high-lift full-flap configuration, CFD method is used to simulate three-dimensional complex flow field, and the effect of grid scale and turbulence model on aerodynamic characteristics of high-lift model is investigated. Using the concept of “hypercube”, a multi-grid structure with different grid densities and high mass around the Trap Wing model was generated. The effect of grid scale on the aerodynamic characteristics of the high-lift model was studied by solving the Reynolds-averaged Navier-Stokes equations. On the basis of this, a medium-scale calculation grid was selected to investigate the simulation capability of Spalart Allmaras and Menter k-ωSST turbulence model for the flow field of high-lift full-configuration flowfield, and the effect of turbulence model on aerodynamic characteristics was analyzed. The results show that the grid strategy has better convergence of the grid. The turbulence model slightly affects the prediction of the pressure coefficient of the airfoil near the wing, and the pressure coefficient predicted by the SA turbulence model is closer to the experimental value than the SST. It is confirmed that the research work provides a reference for the numerical simulation of the large aircraft lifting device.