Multifidelity kinematic parameter optimization of a flapping airfoil.,Physical Review E

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Multifidelity kinematic parameter optimization of a flapping airfoil.
Physical Review E ( IF 2.2 ) Pub Date : 2020-01-01 , DOI: 10.1103/physreve.101.013107
Hongyu Zheng ₁ , Fangfang Xie ₁ , Tingwei Ji ₁ , Zaoxu Zhu ₁ , Yao Zheng ₁

Affiliation

We construct a multifidelity framework for the kinematic parameter optimization of flapping airfoil. We employ multifidelity Gaussian process regression and Bayesian optimization to effectively synthesize the aerodynamic performance of the flapping airfoil with the kinematic parameters under multiresolution numerical simulations. The objective of this work is to demonstrate that the multifidelity framework can efficiently discover the optimal kinematic parameters of the flapping airfoil with specific aerodynamic performance using a limited number of expensive high-fidelity simulations combined with a larger number of inexpensive low-fidelity simulations. We efficiently identify the optimal kinematic parameters of an asymmetrically flapping airfoil with various target aerodynamic forces in the design space of heaving amplitude, flapping frequency, angle of attack amplitude, and stroke angle. Notably, it is found that the angle of attack can significantly affect the magnitude of aerodynamic forces by facilitating the generation of the leading-edge vortex. In the meanwhile, its combination effect with the stroke angle can determine the attitude and trajectory of the flapping airfoil, thus further affect the direction of the aerodynamic forces. With the influence of the streamwise in-line motion, the asymmetrical vortex structures emerge in the wake fields because the streamwise velocities of shedding vortices are different in the upstroke and downstroke. Furthermore, we conduct the kinematic parameter optimization for a three-dimensional asymmetrically flapping wing. Compared to the two-dimensional simulations, we further investigate the flow induced by the vortex ring and its unsteady effects on the vortex structure and aerodynamic performance.

中文翻译：

扑翼的多保真运动学参数优化。

我们为扑翼运动参数的运动学参数优化构建了一个多保真度框架。在多分辨率数值模拟下，我们采用多保真高斯过程回归和贝叶斯优化，以运动参数有效地综合扑翼型的空气动力学性能。这项工作的目的是证明，使用有限数量的昂贵的高保真度模拟与大量廉价的低保真度模拟相结合，多重保真度框架可以有效地发现具有特定空气动力学性能的襟翼翼型的最佳运动学参数。我们有效地确定了具有不同目标空气动力的不对称拍打翼型的最佳运动学参数，该设计空间包括起伏幅度，拍打频率，攻角幅度和冲程角。值得注意的是，发现迎角可以通过促进前沿涡旋的产生来显着影响空气动力的大小。同时，其与行程角的组合作用可以确定拍打翼型的姿态和轨迹，从而进一步影响气动力的方向。在流向直线运动的影响下，非对称涡旋结构在尾流场中出现，这是因为脱落涡流在上游和下游的流向速度不同。此外，我们进行了三维非对称扑翼的运动学参数优化。与二维模拟相比，

更新日期：2020-01-10

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