Abstract
Applying bionic airfoils is essential in enlightening the design of rotating machinery and flow control. Dynamic mode decomposition was used to reveal the low dimensional flow structure of Riblets, Seagull, and Teal bionic airfoils at low Reynolds numbers 1 × 105 and is compared with NACA4412 airfoils. The attack angle of the two-dimensional airfoil is 19°, and the SST k-ω turbulence model and ANSYS fluent were used to obtain the transient flow field data. The sparse identification of nonlinear dynamics reveals the nonlinear correlation between modal coefficients and establishes manifold dynamics. The results show that the bionic airfoil and NACA4412 airfoil have the same type of nonlinear correlation, and the dimension and form of the minimum reduced-order model are consistent. The modal coefficients always appear in the manifold equation in pairs with a phase difference of 90°. The dimension of the manifold equation is two-dimensional, and the absolute value of the coefficient corresponds to the fundamental frequency of airfoil vortex shedding. The reconstructed flow field based on the manifold equation is highly consistent with the numerical simulation flow field, which reveals the accuracy of the manifold equation. The relevant conclusions of this study emphasize the unity of the nonlinear correlation of bionic airfoils.
Funder
China Postdoctoral Science Foundation
Subject
Electrical and Electronic Engineering,Industrial and Manufacturing Engineering,Control and Optimization,Mechanical Engineering,Computer Science (miscellaneous),Control and Systems Engineering
Reference56 articles.
1. Reviews on Design and Development of Unmanned Aerial Vehicle (Drone) for Different Applications;Aabid;J. Mech. Eng. Res. Dev.,2022
2. The starting and low wind speed behaviour of a small horizontal axis wind turbine;Wright;J. Wind Eng. Ind. Aerod.,2004
3. Numerical simulation of flow characteristics behind the aerodynamic performances on an airfoil with leading edge protuberances;Zhao;Eng. Appl. Comp. Fluid,2017
4. Lewthwaite, M.T., and Amaechi, C.V. (2022). Numerical investigation of winglet aerodynamics and dimple effect of NACA 0017 airfoil for a freight aircraft. Inventions, 7.
5. Enhanced performance of airfoil-based piezoaeroelastic energy harvester: Numerical simulation and experimental verification;Tian;Mech. Syst. Signal Process.,2022
Cited by
3 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献