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采用分区拼接网格技术,对DLR-F6机翼/机身/挂架/短舱复杂组合体进行拼接网格分布。并采用Menter SST湍流模型,通过求解Navier-Stokes方程,对该组合体外流场以及发动机短舱内流场进行了一体化数值模拟,与相应风洞实验数据及分区搭接网格计算结果进行了比较与分析,验证了拼接网格技术的高效性与可靠性。同时通过分析对比不同插值方法的计算结果,研究了插值方法对拼接精度的影响;通过分析对比几组不同的拼接网格算例,总结出了3个拼接网格的基本实施准则。证明了拼接网格能够大幅度减小计算网格数目,可以更加灵活地分布网格节点,这样既可以缩短计算时间,又可以降低对内存的需求,提高了计算效率;同时无论整体的力系数,还是局部的压力分布流场细节都能够满足工程精度。
Splitting gridding of DLR-F6 airfoil / fuselage / pylon / nacelle complex system was adopted by using partitioned mosaic grid technology. By using the Menter SST turbulence model, the Navier-Stokes equation is solved to simulate the flow field in the combined body and the flow field in the engine nacelle. The experimental data and the overlapped grid calculation results of the wind tunnel are carried out Comparison and analysis verify the high efficiency and reliability of the splicing grid technology. At the same time, by analyzing and comparing the calculation results of different interpolation methods, the influence of interpolation methods on the accuracy of the splicing is studied. By comparing several groups of different splicing grids, the basic implementation rules of three splicing grids are summarized. It is proved that the splicing grid can greatly reduce the number of computing grids and distribute the grid nodes more flexibly. This not only shortens the computing time but also reduces the memory requirements and improves the computing efficiency. Meanwhile, no matter the overall force coefficient , Or partial pressure distribution flow field details to meet the engineering accuracy.