摘要
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。
In this paper,the transonic flow of Wing/Body/Pylon/Nacelle configuration is simulated by solving Navier-Stokes equations based on structural patched-grid with Menter SST turbulence model.The result is compared with wind tunnel experimental data and the result computed by 1to1 multi-block structural grid.It is proved that patched-grid technology is reliable and efficient.At the same time,interpolation method which influences the simulation is also studied for selection of an appropriate method.At last three basic laws are studied by comparing the result of different patch grids.It is proved that patched-grid can greatly reduce the number of the grids and make the distribution of the grid node freer.By using patched-grid the computation time is shortened and the efficiency is improved,at the same time the engineering precision is fulfilled in both the global force coefficient and the local pressure and streamline of the flow field.
出处
《应用力学学报》
CAS
CSCD
北大核心
2011年第1期69-74,111,共6页
Chinese Journal of Applied Mechanics
关键词
拼接网格
数值模拟
翼/身/架/舱组合体
patched-grid,numerical simulation,Wing/Body/Pylon/Nacelle configuration.
