NASA高升力TrapWing全展模型的数值模拟  

Numerical Simulation of NASA High Lift TrapWing Fullspan Model

作　　者：李萍[1] 李根国[2] 张小柯[3] 杨富军[2] 

机构地区：[1]上海核工程研究设计院,上海200233 [2]上海超级计算中心,上海201203 [3]上海卫星工程研究所,上海200240

出　　处：《力学季刊》2012年第2期249-255,共7页Chinese Quarterly of Mechanics

摘　　要：本文采用计算流体力学(CFD)方法在上海超级计算中心的魔方机上对NASA高升力TrapWing全展模型进行了三维复杂流场的模拟仿真,考察了网格尺度、湍流模型、离散格式对高升力模型气动特性的影响。通过求解雷诺平均的N-S方程,采用多块对接结构网格技术,在与试验结果对比的基础上,研究了k-ω、SST及BSL湍流模型和离散格式对三维高升力TrapWing全展模型气动特性的影响。本文研究结果表明:采用全湍流模拟方式可以较好地模拟主翼的表面压力分布及线性段升、阻力系数,但是流动复杂的前缘缝翼、后缘襟翼和大攻角还需要进一步精细计算;同时还考察了加速比和并行效率。The numerical simulation of NASA high lift configure TrapWing Fullspan model was simulated using CFD method on magic machine of Shanghai Supercomputer Center. The effect of grid size, turbulence modal and difference scheme were discussed. By solving Reynolds averaged Navier-Stokes equation and comparing to the results of wind test, the effect of k-co,SST and BSL turbulence models and difference scheme were carefully studied with structured grids. The numerical results show that pressure distribution of main wing and lift ＆ drag lift coefficient of linear ranger were in good agreement with experiment with full turbulent calculation, whereas leading edge slap and trailing edge flap and aerodynamic characteristics at large attack angle are still need fine computed; The speedup and parallel efficiency were also observed.

关 键 词：高升力构型 湍流模型 离散格式 并行计算 

分 类 号：O355[理学—流体力学]