仿生多孔翼型后缘自噪声数值研究  

Numerical study on bionic porous airfoil trailing edge self-noise

作　　者：雷安鹏 刘勇[1] 余春锦[1] 钟伯文 李克伟 LEI Anpeng;LIU Yong;YU Chunjin;ZHONG Bowen;LI Kewei(School of Aircraft Engineering,Nanchang Hangkong University,330063 Nanchang,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《应用力学学报》2023年第4期769-777,共9页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金资助项目(地区科学基金)(No.11962018);航空科学基金资助项目(No.2018ZA56003)。

摘　　要：采用大涡模拟(LES)和声比拟(AA)结合的方法,在低马赫数条件下,对SD7003多孔翼型自噪声声场进行计算,研究多孔材料在不同来流迎角下对翼型自噪声远场声压的影响规律,并阐述噪声的影响机理。结果表明:LES与AA相结合的方法能够较为准确地计算多孔翼型的边界层特征以及远场声压,且数值模拟结果与实验结果非常吻合。来流迎角为0°时,多孔翼型整体声压级随着渗透率的减小先减小后增大,渗透率为5×10^(-11)m^(2)时多孔材料的降噪效果最佳。多孔翼型整体声压级随着迎角的增大而增大,但多孔材料的降噪效果随着迎角的增大而减小。多孔材料的存在能够有效地削弱翼型表面的大尺度相干结构,使得翼型表面的RMS压强脉动峰值减小,从而抑制翼型远场噪声。Large eddy simulation(LES)and acoustic analogy(AA)method are combined to calculate the sound field of SD7003 porous airfoil self-noise under the condition of a low Mach number.The influence of the porous materials on the far-field sound pressure of the airfoil self-noise is analyzed under the condition of different angle of attact,and the noise reduction mechanism of the airfoil is explained.The results show that the LES/AA method can not only accurately calculate the boundary layer characteristics and the far-field sound pressure of porous airfoil,but the numerical simulation results are in good agreement with the experimental results.When the angle of attact is 0°,the overall sound pressure level of the porous airfoil decreases first and then increases with the decrease of the permeability,and the noise reduction effect of the porous material is the best when the permeability is 5×10^(-11)m^(2).The overall sound pressure level of the porous airfoil increases with the increase of angle of attack,but the noise reduction effect of the porous materials decreases with the increase of angle of attack.The large-scale coherent structures on the airfoil surface are weakened due to the existence of the porous materials,and the peak of the RMS pressure fluctuation on the airfoil surface decreases,thus effectively suppressing the airfoil far-field noise.

关 键 词：仿生翼型 后缘 自噪声 多孔介质 降噪机理 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]