Resolvent analysis of a finite wing in transonic flow
Resolvent analysis of a finite wing in transonic flow
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跨音速流中有限机翼的解析分析
DOI：
10.1017/flo.2023.8
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发表时间：
2023
期刊：
影响因子：
--
通讯作者：
Houtman J
中科院分区：
文献类型：
--
作者：
Houtman J
激波与机翼上的紊流附面层相互作用，首先会导致自持流动的不稳定，最后会导致结构振动。由于跨音速流动物理对现代机翼设计和飞机验证的重要性，它一直是人们研究的重点。在此，我们集中讨论三个主要方面。首先，我们评估一个实际的实施迭代预解算法的线性谐波化身的工业计算流体动力学代码计算最佳的强制和响应模式。这在很大程度上依赖于大型稀疏线性方程组的有效解。其次，我们展示了它的应用程序作为一个预测工具，以检测跨音速抖振流的不稳定性，以及之前的全球稳定性分析可以首先通过弱阻尼本征模态识别其动态，使用NASA的共同研究模型在风洞条件下。第三，我们讨论了它揭示模态物理的能力，通过全局稳定性分析无法识别，揭示了更高频率的尾流和翼尖涡流模式，同时揭示了翼型抖振模式的难以捉摸的有限机翼等效模式。我们证明，早期的计算限制预解式分析，当解决截断奇异值分解使用矩阵形成的方法与直接矩阵分解，已被克服准备工业使用。
Shock waves interacting with turbulent boundary layers on wings can result first in self-sustained flow unsteadiness and eventually in structural vibration. Due to its importance to modern wing design and aircraft certification, the transonic flow physics continue to be investigated intensively. Herein we focus the discussion on three main aspects. First, we assess a practical implementation of an iterative resolvent algorithm in the linear harmonic incarnation of an industrial computational fluid dynamics code for computing optimal forcing and response modes. This heavily relies on the efficient solution of large sparse linear systems of equations. Second, we showcase its application as a predictive tool to detect transonic buffet flow unsteadiness, well before a global stability analysis can first identify its dynamics through weakly damped eigenmodes, using the NASA common research model at wind-tunnel conditions. Third, we discuss its ability to uncover modal physics, not identifiable through global stability analysis, revealing higher-frequency wake and wingtip vortex modes while shedding some light on the elusive finite wing equivalent of the aerofoil buffet mode. We demonstrate that earlier computational limitations of resolvent analysis, when solving the truncated singular value decomposition using matrix-forming methods with direct matrix factorisation, have been overcome ready for industrial use.