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Investigations on high-fidelity low-dissipation scheme for unsteady turbulent separated flows

机译：对不稳定湍流分离流量的高保真低耗散方案的研究

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Unsteady turbulent separated flow widely exists in aerospace vehicles and has become a major research topic. For the precise turbulent flow prediction, efficient and accurate numerical methods are the premise and foundation. However, most shock-capturing schemes designed for compressible flows have some difficulties in low-speed flow regions, and reduce the reliability when simulating unsteady turbulent separated flow with rich low Mach number features. Thus, the paper proposes a high-fidelity low-dissipation scheme termed LD-Roe2 and investigates the performances of the novel approach in unsteady turbulent separated flow simulations using the Hybrid Reynolds Averaged Navier-Stokes Equations/Large Eddy Simulation Approach (Spalart-Allmaras Delayed Detached Eddy Simulation). Numerical results including flow over a circular cylinder at subcritical Reynolds number and flow over tandem cylinders, demonstrate that the novel low-dissipation scheme can better simulate the unsteady separated flow and depicts finer smaller-scale vortical structures compared with traditional numerical schemes. It is expected to provide a more accurate and applicable numerical solution for the refined turbulent prediction. (C) 2021 Elsevier Masson SAS. All rights reserved.
机译：航空航天车辆中的不稳定湍流分离流量广泛存在，已成为一个主要的研究主题。对于精确的湍流流量预测，有效和准确的数字方法是前提和基础。然而，对于可压缩流设计的大多数冲击捕获方案在低速流量区域方面具有一些困难，并且在模拟具有丰富低马赫数特征的不稳定湍流分离流时降低可靠性。因此，本文提出了一种称为LD-RoE2的高保真低耗散方案，并研究使用Hybrid Reynolds平均Navier-Stokes方程/大涡仿真方法（Spalart-Allmaras延迟）独立涡流模拟）。数值结果包括在亚临界雷诺数的圆柱体上的流动，并在串联圆柱体上流动，表明新的低耗散方案可以更好地模拟不稳定的分离流程，并与传统的数值方案相比，描绘更细的小规模涡流结构。预计将为精细湍流预测提供更准确和适用的数值解决方案。 （c）2021 Elsevier Masson SAS。版权所有。

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