摘要
本文选用DLR-F6翼身组合体模型,分析了不同类型网格及湍流模型对机翼表面压力分布和翼根分离区的预测精度影响。分析结果表明,六面体、四面体和多面体网格预测得到的机翼表面压力分布和翼根分离区大小基本一致,在保证相同计算结果精度的前提下,多面体网格使用的网格单元数量最少,计算效率最高,且网格生成十分方便。此外,S-A,SST和RSM湍流模型均能较准确地预测出DLR-F6机翼表面压力分布,但S-A和SST湍流模型预测得到的翼根处分离区较实验结果明显偏大,而RSM湍流模型预测结果与实验结果更加吻合。从湍流模型构造上分析发现,S-A和SST模型基于湍流各向同性假设,忽略了角区分离流动处的雷诺正应力之差,而RSM湍流模型由于反映了雷诺应力的各向异性,因此预测得到的翼根处分离区与实验结果更加接近。
The DLR-F6 wing-body configuration is used to analyze the effects of different kinds of computational meshes and turbulence models on the prediction accuracy of the wing surface pressure distribution and wing root separation zone. The computational results show that the distribution of wing surface pressure from hexahedral,tetrahedral and polyhedral meshes are almost the same,and so does the separation zone in the wing root. Compared with the hexahedral and tetrahedral meshes,the polyhedral mesh has the same computational accuracy,but the lowest number of grid cells and the highest calculation efficiency. In addition,the grid generation is very convenient for polyhedral mesh compared with hexahedral mesh. Furthermore,the S-A,SST and RSM turbulence models can accurately predict the surface pressure distribution on DLR-F6 wing. However,the separation zone near the wing root predicted by the S-A and SST turbulence models is larger than the experiment,while the RSM turbulence model predicts the same results as the experiment. From the analysis of the formulation of turbulence models,it is found that the S-A and SST models are based on isotropic turbulence assumption,neglecting the difference of Reynolds normal stress at the corner separation. However,the RSM turbulence model which has considered the anisotropy in turbulence flow,can predict accurate separation zone near the wing root.
出处
《航空兵器》
2017年第5期60-67,共8页
Aero Weaponry
基金
航空科学基金项目(20130179002)
