Abstract: 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.