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中文摘要：
为了研究阻力计算精度并考察网格和湍流模型对翼身组合体构型气动特性的影响,通过求解雷诺平均Navier-Stokes方程耦合Spalart-Allmaras和Baldwin-Lomax湍流模型,数值模拟DLR-F4翼身组合体流场.使用＂超立方体＂概念构建绕DLR-F4翼身组合体的高质量多块结构拼接网格,通过网格细分来研究网格密度对计算结果的影响.结果表明：湍流模型和网格密度对升力影响较小,对阻力影响较大,网格密度对压力系数分布影响甚微;适当地缩小第一层网格到物面的距离,增加物面法向网格点数能改善阻力计算精度.
英文摘要：
The DLR-F4 wing-body model is a simplified geometric simulation of current subsonic commercial aircraft intended to help evaluate simulations predicting aircraft drag.The accuracy of computed drag around it was investigated,and in particular,the effects of grid and turbulence models were analyzed.This was done by solving the Reynolds-averaged Navier-Stokes equations（RANS） coupled with the Spalart-Allmaras and Baldwin-Lomax turbulence models.A high quality multi-block structured patched grid around the wing-body configuration was generated using the hypercube concept.Mesh refinement was performed to investigate the effects of the grid＇s density.The results showed that computed lift was slightly affected by turbulence models and the grid＇s density.Computed drag was significantly affected by both turbulence models and the grid＇s density.The pressure coefficient distribution was slightly affected by the grid＇s density.This research showed that the accuracy of computed drag can be improved by decreasing the grid interval between the object plane and the first-layer mesh as well as by properly increasing the density of the grids.
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