HyperFLOW 软件数值模拟TrapWing 高升力外形

Numerical research of NASA high-lift trap wing model based on HyperFLOW

采用High-Lift研讨会提供的梯形翼外形(TrapWing),利用自主研发的基于结构、非结构网格的通用CFD软件HyperFLOW进行了数值计算,以评估其对复杂外形低速流的模拟能力。分别采用了三套不同拓扑结构的计算网格,包括两套非结构/混合网格和一套多块结构网格,每套网格又分为粗、中、细三种密度不同的网格数量以考察其网格收敛性。利用Richardson插值法,对计算结果开展了可信度分析。结果表明,不管是结构网格还是非结构网格,HyperFLOW均建立了可接受的可信度;对于高升力外形数值模拟,SA湍流模型要比SST湍流模型模拟的更准确;在失速迎角附近,现有的二阶精度解算器仍需持续改进。

Up to date,simulation of subsonic flows over the high lift device is still a chal-lenge,especially for the cases with higher angles of attack.In order to evaluate the ability of Hy-perFLOW,an in-house CFD software for subsonic turbulence flow over complex geometries based on structured and unstructured grids,the NASA high lift trap wing model is selected and investigated.Two cases discussed in the NASA high-lift workshop are considered on three types of grids,i.e.two unstructured or mixed grids,and one multi-block structured grid.The simula-tions on coarse,medium and fine grids for each type are carried out to access the performance of grid convergence.The numerical results are analyzed using Richardson extrapolation method, and compared with the experimental data and the results by other famous CFD codes in the world.The comparison demonstrates that HyperFLOW has a good property of grid convergence on different grids.As the statistical conclusions of the NASA high-lift workshop,the numerical results are acceptable within the linear part of the aerodynamic forces in the regime of lower and medium angles of attack.However,it is still a challenge for the prediction of the cases in higher angles of attack,especially for the cases near stall.