The unsteady transonic aerodynamics of a wing-body configuration is investigated by solving the Unsteady Reynolds-averaged Navier-Stokes equations closed with the full Reynolds Stress Model. This work presents the prediction of flow field characteristics during deep shock-buffet penetration of a transport aircraft-representative geometry. Mach number of 0.85, and Reynolds number of 5 million based on the mean chord, are selected to reproduce experimental test conditions that serve as validating datasets. The results obtained give information about both surface and flow field shock-buffet dynamics. An unsteady shock front is observed on the suction side of the wing which gives birth to the so-called buffet cells. Flow field characteristics are dominated by the presence of lambda-shaped shocks and fully separated boundary layer over a significant part of the wing.

中文翻译：

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跨音速飞机减震器中的非稳态减震前波度

通过求解由完整雷诺应力模型封闭的非稳态雷诺平均Navier-Stokes方程，研究了机翼机体的非稳态跨音速空气动力学。这项工作提出了运输飞机代表性几何图形的深冲击击穿过程中流场特性的预测。选择马赫数为0.85，基于平均和弦的雷诺数为500万，以重现用作验证数据集的实验测试条件。获得的结果提供了有关表面和流场冲击波动力学的信息。在机翼的吸力侧观察到一个不稳定的冲击前部，从而产生了所谓的“自助餐室”。