NLR-7301高升力翼型绕流评估计算  

CFD Validation for High-lift Flow over NLR-7301 Airfoil

作　　者：李立[1] 麻蓉[1] 梁益华[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2014年第3期12-15,共4页Aeronautical Computing Technique

基　　金：国家973计划项目资助(2009CB723804);中欧航空科技合作专项项目资助(FP7/2010-266326)

摘　　要：探讨了在二维高升力多段翼型绕流计算中附面层网格采用各向异性三角形网格的技术。通过对经典的NLR-7301两段翼型绕流的计算,从数值计算角度评估了自研混合网格雷诺平均N-S方程求解软件对该类型附面层网格的解算能力。通过与确认试验数据对比,在附面层采用各向异性三角形网格进行二维高升力多段翼型绕流计算,其结果具有较高的可信度。在此基础上,采用同样策略,评估了多段翼型绕流计算中翼型后缘的几何处理、湍流模型选取等关键CFD要素对计算结果的影响。The application of anisotropic triangular mesh behind boundary layer for two-dimensional high-lift multiple segment airfoils is discussed in this paper .The computation is performed on flow over the classic NLR-7301 high-lift airfoil to evaluate an in-house RANS solver for such type of hybrid unstructured meshes .The results are compared with validated experimental data ,which shows that credible numerical results can be obtained on the mesh with anisotropic triangles behind the boundary layer .Based on these observations ,effects of geometric treatment and turbulence models for high-lift device modeling are evaluated .

关 键 词：高升力系统 多段翼型绕流 NLR7301 各向异性网格 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]