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为了进一步研究飞机远场尾涡,提供网格分配及湍流模型的参考,并为整机模拟提供必要的参考依据,通过基于Ansys Fluent的数值模拟方法,研究了NACA0012机翼的近场翼尖涡流场,采用有限体积法求解不可压缩雷诺平均Navier-Stokes方程,其中雷诺应力项分别以S-A和Realizable k-ε模型封闭,模拟了近场翼尖涡卷起的过程,分析了机翼表面压力以及涡核参数,包括轴向涡量、涡核位置、涡核粘性等,并与风洞实验结果进行了对比。结果分析表明:基于局部O-网的六面体网格,RKE模型要优于S-A模型,与实验值更为吻合。
In order to further study the vortex in the far field of the aircraft and provide reference for grid distribution and turbulence model, and provide the necessary reference for the whole machine simulation, the near-field wingtip vortex of NACA0012 wing is studied by the numerical simulation method based on Ansys Fluent Field, the incompressible Reynolds average Navier-Stokes equation is solved by the finite volume method. The Reynolds stress term is closed with the SA and Realizable k-ε models respectively. The process of the near-field wing tip coiling is simulated. The parameters of vortex core, including the axial vorticity, vortex core position and vortex core viscosity, are compared with the wind tunnel experimental results. The result shows that the RKE model is better than the S-A model based on the local O-mesh hexahedral mesh, which is in good agreement with the experimental data.