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Control of flow instabilities in an open aircraft bay model cavity

机译:控制开放式飞机机舱模型腔中的流动不稳定性

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Adjoint-based passive flow control is applied to damp the instabilities arising in the three-dimensional incompressible flow over a realistic open cavity with geometric ratio 6:2:1 at low Reynolds number. Direct numerical simulation and TriGlobal stability analysis are performed to identify the complex three-dimensional flow structures corresponding to flow instabilities in this flow. The instability onset is caused by the linear growth of a three-dimensional shear layer mode and the structural sensitivity of this leading global mode is identified by means of an adjoint analysis. Based on this information, we perform a small base flow modification inside the structural sensitivity region by collocating a small rod at the interface of the cavity. Results from this passive control systems demonstrate the substantial reduction on the amplitude of the oscillation and the effective suppression of the three-dimensional vortex oscillation.
机译:在低雷诺数下,使用基于伴随的被动流量控制来抑制在几何比例为6:2:1的实际开放腔体上三维不可压缩流中产生的不稳定性。执行直接数值模拟和TriGlobal稳定性分析,以识别与该流中的流不稳定性相对应的复杂三维流结构。不稳定的起因是三维剪切层模态的线性增长引起的,这种领先的全局模态的结构敏感性是通过伴随分析确定的。基于此信息,我们通过在腔体的界面处并置一个小杆来在结构敏感区域内进行小的基流修改。该无源控制系统的结果表明,可以大幅降低振荡幅度并有效抑制三维涡旋振荡。

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