【摘要】 为了获得具有优异气动性能的翼型仿生设计，采用数值方法研究了NACA0012基线翼型和受鸽翼羽毛槽结构启发的仿生翼型的气动性能和噪声特性。本文以鸽子翅膀为仿生原型，基于逆向工程技术和三维扫描结果提取了鸽子翅膀的结构参数。首先针对NACA0012翼型，重构了具有羽毛槽非光滑结构的仿生翼型。考虑鸽子滑翔时不同的飞行姿态，采用数值计算方法研究了攻角AOA对仿生翼型气动性能的影响，对比分析了NACA0012翼型与仿生设计翼型的气动性能和噪声特性。在仿生翼型设计中，槽宽与凸起半径的比值分别设计为6:1,7:1和8:1，以揭示不同尺寸的羽毛沟槽配置对仿生翼型流动性能的影响。结果表明，与NACA0012翼型相比，即使在高攻角α=17°下仿生翼型也具有较好的流动控制能力。当槽宽与凸起半径之比为7:1时，仿生翼型的气动噪声最低。这表明近尾缘区域表面沟槽结构对翼型气动性能和噪声有着较大程度的影响，本文研究试图通过揭示鸽子翅膀表面羽毛沟槽的流动控制机理，为翼型设计和优化提供有益的参考。更多还原

【Abstract】 To obtain the bionic design of the airfoils with excellent aerodynamic performance, the aerodynamic performance and noise characteristics of the NACA0012 baseline airfoil and the bionic airfoil inspired by the feather slots structure of the pigeon wing are studied by the numerical method. In this paper, taking the pigeon wings as the bionic prototype, the structural parameters of the pigeon wings is collected based on the reverse engineering technique and the three-dimensional scanning results. Firstly, the bionic airfoil with the non-smooth structures of feather slots is established based on NACA0012 baseline airfoil. And then, the effects of the angle of attack(AoA) on the aerodynamic performance of the bionic airfoils under the condition of pigeon gliding flight are investigated. Based on the numerical results, the aerodynamic performance and noise characteristics of the NACA0012 airfoil and the designed bionic airfoil are analyzed and compared. The ratios of the groove width to the radius of the protuberances of 6:1, 7:1 and 8:1 are designed respectively in the bionic airfoil to reveal the influences of the different sizes of feather slots configuration on the aerodynamic performance of bionic airfoil. The results show that compared with the NACA0012 baseline airfoil, the bionic airfoil has better flow control ability, excellent aerodynamic performance and lower noise even at the high angle of attack, α=17°.When the ratio of groove width to the radius of the protuberances is 7:1, the aerodynamic noise of the bionic airfoil is the lowest among the three bionic models. The results indicate that the surface groove structure near the trailing edge has a significant impact on the aerodynamic performance and noise of the airfoil. Through the present study, we try to reveal the flow control mechanism of the feather slots of pigeon wings, so as to provide some valuable references for the design of bionic airfoils.更多还原