摘要
基于混合求解法,通过对声源区计算域进行分区,研究了二维多段翼不同部件对远场声压级的贡献,给出了声场分布和远场指向性,发现前缘缝翼噪声和主翼尾缘噪声对远场的贡献较小,襟翼后缘噪声的贡献在总声压级中占主导地位,是值得关注的噪声来源。
Based on hybrid-solving method, by dividing the sound field computational domain into four different parts, the influence of different parts of the 2-D multiple elements airfoil on far field sound pressure level was in- vestigated and the sound field mapping and far field directivity were presented. It was found that the noise contribution of slat and main airfoil on far field is far less than that of flap trailing edge, which dominates for overall sound pressure level and should be paid priority attention.
出处
《民用飞机设计与研究》
2013年第2期8-12,44,共6页
Civil Aircraft Design & Research
关键词
计算气动声学
多段翼
气动噪声
混合求解法
Computational Aerodynamic Acoustics
Multiple Elements Airfoil
Aerodynamic Generated Noise
Hy- brid-Solving Method
