Optimal Actuator Selection for Airfoil Separation Control
Optimal Actuator Selection for Airfoil Separation Control
复制标题
机翼分离控制的最佳执行器选择
DOI：
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发表时间：
2018
期刊：
影响因子：
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通讯作者：
G. Jacobs
中科院分区：
文献类型：
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作者：
D. Bhattacharjee;Maziar S. Hemati;B. Klose;G. Jacobs
为了减轻流动分离和改善气动性能，已经开发了许多主动流动控制策略。大多数研究都集中在优化控制动作为一个给定的执行器配置，然而，执行器的位置是密切相关的可实现的性能。在本文中，我们制定了一个系统的方法来确定最佳的致动器位置分离控制的数值和实验流体数据稳定和不稳定的系统。已经进行了高保真数值流体模拟，以计算升力和分离角响应的局部体积力驱动施加在六个不同的位置上的翼型的上表面上的脉冲。然后，这些脉冲响应数据用于确定致动器位置，该致动器位置可以以最小量的输入能量将系统输出驱动到任意值。研究结果表明，控制升力和分离角的最佳作动器位置是不相同的。
Many active flow control strategies have been developed to mitigate flow separation and improve aerodynamic performance. Most studies have focused on optimizing the control action for a given actuator configuration; however, actuator placement is intimately tied to achievable performance. In this paper, we formulate a systematic approach for determining the optimal actuator location for separation control from numerical and experimental fluids data for both stable and unstable systems. High-fidelity numerical fluids simulations have been performed to compute the lift and separation-angle responses to a pulse of localized body-force actuation applied at six distinct locations on the upper surface of the airfoil. These pulse response data are then used to determine the actuator location among the set that can drive the system output to an arbitrary value with the minimum amount of input energy. The results of this study indicate that the optimal actuator locations for controlling lift and separation angle are not identical.