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针对跨音速运输机经典算例DLR—F6翼身组合体模型,采用CFD方法对其气动特性进行了黏性流动数值模拟,流动模型为雷诺平均N-S(RANS)方程。首先采用“超立方体”概念生成绕DLR—F6翼身组合体的高质量多块结构拼接网格,研究网格拓扑结构对气动特性的影响。在此基础上通过网格细分和粗分考查了网格密度对计算结果的影响,最后进行了湍流模型的影响研究。通过与实验数据对比分析,得出了适宜DLR—F6翼身组合体跨音速黏性流动的计算网格,并总结出了能较好模拟其跨音速流场特性的湍流模型。结果表明:网格拓扑结构的合理设计会对计算结果产生一定的影响。网格密度对机翼表面压力分布没有明显影响,但对阻力系数影响显著。湍流模型对机翼表面压力系数分布的影响主要体现在激波位置上,对翼根处的分离也有一定的影响。SST模型计算的气动力系数比SA模型接近实验值。
Aiming at the DLR-F6 wing-body combination model of transonic supersonic transporter, CFD method was used to simulate its viscous flow. The flow model is the Reynolds-averaged Navier-Stokes equations. Firstly, a high-quality multi-block structure mosaic grid around the DLR-F6 wing-body assembly is generated by using the concept of “hypercube” to study the influence of the grid topology on the aerodynamic characteristics. Based on this, the effect of grid density on the calculation results is investigated by the mesh subdivision and the rough subdivision. Finally, the influence of turbulence model is studied. By comparing with the experimental data, a computational grid suitable for the transonic viscous flow of the DLR-F6 wing-body assembly is obtained, and a turbulence model that can better simulate the transonic flow field is summarized. The results show that the reasonable design of the grid topology will have a certain impact on the calculation results. The grid density has no obvious effect on the pressure distribution on the wing surface, but has a significant effect on the drag coefficient. The influence of turbulence model on the distribution of pressure coefficient on the wing surface is mainly reflected in the location of the shock wave and also has some influence on the separation of the wing root. The aerodynamic coefficient calculated by SST model is close to the experimental value than the SA model.