The present article assesses the capability of the partially averaged Navier-Stokes (PANS) method to reproduce accurately the self-sustained shock oscillations, also known as transonic buffet, occurring on airfoils and wings at transonic regime under certain conditions of Mach number and angle of attack. The test case under analysis is an OAT15A unswept wing at Mach number and Reynolds number . The three-dimensional flow is studied by accounting for the wind tunnel walls adopted in the experiments of Jacquin et al. in the simulations. The computations on a large-span, confined configuration reveal a strong three-dimensionality of the flow both before and after the buffet onset. Attention is paid to the comparison with unsteady Reynolds-averaged Navier Stokes (URANS) results, to show the benefits of PANS in resolving flow unsteadiness at different flow resolutions, especially on affordable CFD grids, at limited additional cost. In this context, the role of the mesh metrics and the local turbulence level in the formulation of the model is described, as well as the relation of this latter with the spatiotemporal discretization used for the numerical simulations. The aim is to extend the use of PANS and obtain accurate predictions of flow cases involving shock-wave boundary layer interactions without expensive approaches.

中文翻译：

---

使用部分平均纳维-斯托克斯方法进行跨音速抖振模拟


本文评估了部分平均纳维-斯托克斯 (PANS) 方法准确再现自持冲击振荡（也称为跨音速抖振）的能力，该振荡在特定马赫数和角的条件下在跨音速状态下发生在翼型和机翼上。攻击。所分析的测试案例是马赫数和雷诺数下的 OAT15A 无后掠翼。通过考虑 Jacquin 等人的实验中采用的风洞墙来研究三维流动。在模拟中。对大跨度、受限结构的计算揭示了抖振发生之前和之后的流动的强烈三维性。重点关注与非稳态雷诺平均纳维斯托克斯 (URANS) 结果的比较，以显示 PANS 在以有限的额外成本解决不同流量分辨率下的流动不稳定问题方面的优势，特别是在经济实惠的 CFD 网格上。在这种情况下，描述了网格度量和局部湍流水平在模型制定中的作用，以及后者与用于数值模拟的时空离散化的关系。目的是扩展 PANS 的使用并获得涉及冲击波边界层相互作用的流动情况的准确预测，而无需昂贵的方法。