摘要
利用具有全消声环境的低速开口风洞研究了采用翼型尾缘刷毛来控制翼型噪声的方法,研究了不同迎角情况下不同长度和间距刷毛对翼型远声场气动噪声的影响以及翼型表面压力的影响,并把该方法与锯齿尾缘降噪方法对比,研究了不同工况下两种降噪方案对降噪效果的影响。实验结果表明,翼型尾缘附加刷毛是一种可行的降噪方案,尤其对中低频段具有比较明显的降低效果;降噪效果与刷毛的间距和长度有关;尾缘刷毛与锯齿尾缘相比具有更优的降噪效果。附加刷毛对翼型壁面动态压力载荷的影响较小。
Some experimental investigations are done on suppressing the airfoil noise by trailing edge brushes.All the experiments are carried out in the low-speed open jet wind tunnel which is in the anechoic chamber.The study is focused on the influence of the angle of attack of the airfoil on the far field noise and the airfoil surface pressure.In addition,the effect of the proposed method and that of the serrated trailing edge method on noise reduction are compared under different operating conditions.The result shows that the trailing edge brush is a feasible way to reduce the airfoil noise,especially for the low frequency component.It is revealed that the noise reduction is related to the length and interval of brush.And the trailing edge brushes are superior to a serrated trailing edge in noise reduction.Meanwhile,trailing edge brushes have little effect on the surface pressure of the airfoil.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2011年第5期612-616,共5页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家重点基础研究发展计划("九七三"计划)(2007CB714604)资助项目
关键词
尾缘噪声
刷毛型尾缘
远声场
翼型表面动态压力
trailing edge noise
trailing edge brushes
far field noise
airfoil surface dynamic pressure
