Flow Around a Leading Edge Slat: Part II — Cove Flow Dynamics via Snapshot POD
Flow Around a Leading Edge Slat: Part II — Cove Flow Dynamics via Snapshot POD
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前缘缝翼周围的流动：第二部分 — 通过 Snapshot POD 进行 Cove 流动动力学
DOI：
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发表时间：
2014
期刊：
影响因子：
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通讯作者：
Joseph W. Hall
中科院分区：
文献类型：
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作者：
Stephen J. Wilkins;P. Richard;Joseph W. Hall
本文用本征正交分解方法研究了前缘缝翼内凹的流动特性。来自缝翼尖端的剪切层包含了流动中大部分的湍流动能。重建与前10个POD本征模式进行说明，几个较小的涡度区域内的剪切层持续。取决于雷诺数和攻角，剪切层可以撞击在主翼元件的前缘上，在缝翼内凹处卷起，或者通过缝翼后缘和机翼前缘之间的差距喷射。剪切层和剪切层内较小特征的这种不稳定冲击可能导致非常强的声偶极子源。Copyright © 2014 by ASME
The dynamics of flow within the cove of a leading edge slat has been investigated using Proper Orthogonal Decomposition by the method of snapshots. The shear-layer that originates from the slat cusp contains a large proportion of the turbulent kinetic energy within the flow. Reconstructions performed with the first 10 POD eigenmodes illustrates that several smaller regions of vorticity persist within the shear-layer. Depending on the Reynolds number and the angle of attack, the shear-layer can impinge upon the leading edge of the main wing element, roll up within the slat cove, or be ejected through the gap between the slat trailing edge and the leading edge of the wing. This unsteady impingement of both the shear-layer, and the smaller features within the shear-layer could result in a very strong acoustic dipole source.Copyright © 2014 by ASME