In this research, the sound emission from the aerodynamic flow around the three-dimensional NACA-0012 airfoil has been calculated. Transient Navier-Stokes equations have been applied to calculate pressure fluctuations in combination with the large eddy simulation method. The sound intensity is obtained using the Fox-Williams and Hawkins acoustic analogy equations. The solution results have been validated using experimental data. For the wind tunnel flow, the effective angle of attack changes in the vicinity of the walls. For this purpose, the local angle of attack has been corrected. The results show that with a 1.3-degree increase in the angle of attack, the sound pressure level increases by 1.64 decibels. Also, the correction applied to the angle of attack has improved the conformity of the simulation results with the experimental data. After that, sound attenuation due to distance has been investigated and almost one decibel per meter decrease in the overall average sound pressure level-OASPL was observed. In the investigation of sound propagation at different angles, bipolar waves were also recognized as the dominant acoustic mechanism.