摘要
基于NACA0018翼型,将波状前缘、锯齿尾缘和表面脊状3种仿生结构进行耦合,形成WSR翼型,并采用大涡模拟和FW-H方法研究了WSR翼型在不同雷诺数和攻角下的流场和噪声特性。结果表明:在小攻角、低雷诺数下WSR翼型可降低噪声5 dB左右;在大攻角下,锯齿尾缘结构加剧了尾缘处流动掺混,改变了尾迹涡结构,降低了翼型尾缘处的涡量,进而使噪声降低8 dB左右。
Based on the NACA0018 airfoil,the WSR airfoil was formed by coupling wavy leading edge,serrated trailing edge and ridged surface.The flow field and noise characteristics of WSR airfoil at different Reynolds numbers and angles of attack were studied by large eddy simulation and FW-H method.Results show that at low angle of attack and low Reynolds number,the WSR airfoil can reduce the instability noise by 5 dB.At high angle of attack,the serrated trailing edge structure would intensify flow mixing at trailing edge,change wake vortex structure,reduce vorticity at trailing edge of airfoil,and finally noise would be reduced by 8 dB.
作者
谢鸣
杨爱玲
陈二云
张文清
XIE Ming;YANG Ailing;CHEN Eryun;ZHANG Wenqing(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai 200093,China;Key Laboratory of Multiphase Flow and Heat Transfer in Power Engineering,Shanghai 200093,China;Key Lab of Intelligent and Green Flexographic Printing,Shanghai Publishing and Printing College,Shanghai 200093,China)
出处
《动力工程学报》
CAS
CSCD
北大核心
2021年第7期572-580,共9页
Journal of Chinese Society of Power Engineering
基金
国家自然科学基金资助项目(51106099,50876072)。
关键词
耦合仿生
翼型
边界层
压力脉动
气动噪声
coupled bionic
airfoil
boundary layer
pressure fluctuation
aerodynamic noise
