• 论文 •

翼型湍流尾缘噪声半经验预测公式改进

1. 北京航空航天大学 能源与动力工程学院, 北京 100083
• 收稿日期:2016-01-21 出版日期:2017-01-20 发布日期:2016-04-18
• 通讯作者: 李晓东,E-mail:lixd@buaa.edu.cn E-mail:lixd@buaa.edu.cn
• 作者简介:柏宝红,男,博士研究生。主要研究方向:气动声学;李晓东,男,博士,教授。主要研究方向:气动声学、计算气动声学。
• 基金资助:
国家“973”计划（2012CB720202）；国家自然科学基金（51476005）

Improvement of airfoil turbulent trailing-edge noise semi-empirical prediction formulation

BAI Baohong, LI Xiaodong

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
• Received:2016-01-21 Online:2017-01-20 Published:2016-04-18
• Supported by:
National Basic Research Program of China (2012CB720202); National Natural Science Foundation of China (51476005)

Abstract: The traditional BPM semi-empirical prediction airfoil turbulent boundary layer trailing edge noise was improved. The traditional BPM semi-empirical prediction formulation overpredicts the spectra in high frequency range at high angle of attack or for thick airfoil. It is found that it was mainly caused by the overestimation of the noise contribution from pressure side source through the analysis and comparison between the traditional BPM semi-empirical prediction formulation and Howe's trailing-edge noise theoretical model. Then the ratio of noise contribution from suction side and pressure side source is improved to the square power of boundary displacement thickness rather than the one power appeared in the traditional BPM semi-empirical prediction formulation. The improved BPM semi-empirical prediction formulation is employed in the airfoil turbulent boundary layer trailing-edge noise prediction, which shows that better results can be obtained from the improved BPM semi-empirical prediction formulation for NACA0012 airfoil at high angle of attack. The prediction for wind turbine airfoil DU-96-W-180 is improved significantly by improved BPM semi-empirical prediction formulation.