摘要
为进一步提升飞机翼型的气动和声学性能,提出了主/被动耦合流动控制方法,即前缘旋转圆柱+尾缘变弯,通过大涡模拟(LES)和Ffowcs Williams-Hawkings(FW-H)方法,深入研究了此控制方法对NACA 0012翼型在不同来流攻角下的气动性能影响。同时,深入分析了翼型在18°大攻角时的非定常流场和声场特性,以及该控制方法的降噪效果和物理机制。研究结果表明:主/被动耦合控制方法(前缘旋转圆柱+尾缘变弯)能够显著提升翼型的气动和声学性能,最高可降低气动噪声峰值约24 dB,该控制策略通过有效抑制大尺度分离涡,从而优化了翼型的气动声学性能。
To further enhance the aerodynamic and acoustic performance of the airfoil,this paper proposes an active/passive coupled flow control method—combining a rotating leading-edge cylinder with a morphing trailing edge.Using large eddy simulation(LES)and the Ffowcs Williams-Hawkings(FW-H)method,this study examines the impact of this control approach on the aerodynamic performance of a NACA 0012 airfoil under different angles of attack.In-depth analyses are conducted on the unsteady flow field and acoustic field characteristics of the airfoil at a high angle of attack(18°),as well as the noise reduction effects and underlying mechanisms of the control method.The results indicate that the active、passive coupled control strategy(leading-edge rotating cylinder+morphing trailing edge)significantly improves the airfoil's aerodynamic and acoustic performance,achieving a maximum reduction in peak aerodynamic noise of approximately 24 dB.This control strategy optimizes the aeroacoustic performance of the airfoil by effectively suppressing large-scale separation vortices.
作者
保女子
Bao Nyuzi(Anhui Xinhua University,Hefei Anhui 230088,China)
出处
《机械管理开发》
2025年第5期1-3,6,共4页
Mechanical Management and Development
基金
安徽新华学院校级科研项目(2022zr015)。
关键词
翼型
主/被动控制
攻角
流动分离
气动性能
气动噪声
airfoil
active、passive control
angle of attack
flow separation
aerodynamic performance
aerodynamic noise
