Airfoil noise reduction using morphing trailing edge
Airfoil noise reduction using morphing trailing edge
复制标题
使用变形后缘降低机翼噪声
DOI：
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发表时间：
2014
期刊：
影响因子：
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通讯作者：
P. Weaver
中科院分区：
文献类型：
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作者：
Q. Ai;M. Azarpeyvand;Xavier Lachenal;P. Weaver
介绍并研究了一种基于变形结构的新型翼型降噪技术。为了实现高空气动力学性能并降低噪音，开发了一种基于弯曲刚度定制零泊松比蜂窝芯的新变形襟翼概念。使用二维有限元模型研究变形结构对内部驱动力的响应。在本研究中，弦长 1.3m 的 NACA 63-418 翼型安装了变形襟翼。利用Xfoil和BPM半经验翼型噪声预测模型研究了翼型的气动和声学性能。针对翼型后缘压力侧和吸力侧的轮廓和曲率变化的影响提供了参数研究。在不同马赫数和攻角下研究了所提出方法的有效性。结果表明，后缘变形后翼型的空气动力学和声学性能将显着提高。此外，变形襟翼设计的初步优化表明，通过改变蜂窝芯沿弦的弯曲刚度，可以定制变形轮廓，从而改善空气动力学性能并显着降低低频噪声。
A novel airfoil noise reduction technique, based on morphing structures, has been introduced and investigated. In order to achieve high aerodynamic performance and reduce the noise, a new morphing flap concept based on a bending stiffness tailored honeycomb core with zero Poisson’s ratio has been developed. The response of the morphing structure to an internal actuation force is investigated using a two-dimensional finite element model. In this study, a NACA 63-418 airfoil of chord 1.3m has been fitted with the morphing flap. The aerodynamic and acoustic performance of the airfoil is studied using Xfoil and the BPM semi-empirical airfoil noise prediction model. A parametric study is provided for the effects of the changes to the profile and curvature of the pressure and suction sides of the airfoil trailing edge. The effectiveness of the proposed method is investigated at different Mach numbers and angles of attack. Results have shown that both the aerodynamic and acoustic performance of the airfoil will significantly improve as a result of the morphing trailing edge. Also, the preliminary optimization of the morphing flap design has shown that by changing the bending stiffness of the honeycomb core along the chord, the morphing profile can be tailored, leading to aerodynamic performance improvement and significant noise reduction at low frequencies.