摘要
本文运用面无法和涡声理论数值来研究具有旋涡的ＮＡＳＡＧＡ（Ｗ）－１型翼型绕流的流场和辐射声场，这对于提高透平机械的效率及降低辐射噪声很有帮助。采用作者积累的关于面无法的一些计算技巧，首先成功地求解了不同攻角来流时的流场，再用涡声理论计算了涡旋绕过翼型时声压场的变化及声源的指向性，最后给出了有关这种流动噪声的发声机理和声源特性的一些有用的结论。
The panel method and the vortex sound theory were used to study the flowfield and the acoustic field caused by uniform flow with a vortex around NASA GA(W)-1 airfoil numerically. It is very useful for improving efficiency of turbomechine and reducing its radiated noise. By use of several know--hows of panel method accumulated through our numerical experiments, the flowfields at different attack angles were successfully solved. After that, the variation of acoustic pressure in the course of a vortex past the practical airfoil and the orientation of sound source were demonstrated by using the vortex sound theory. Finally, some useful conclusions related by the mechanism of sound generation and the characteristics of sound source about this type of flow noise were drawn out.
出处
《声学学报》
EI
CSCD
北大核心
1995年第3期183-190,共8页
Acta Acustica
基金
国家自然科学基金
