This paper presents computations for prediction of the acoustic sound generated from an airfoil using the Large Eddy Simulations. To validate our calculations, a NACA 0012 airfoil with the angle of attack 15.6◦ placed in a freestream flow is studied where the Reynolds number based on the chord length is 5 ×105 and the Mach number is 0.2. This study employs the hybrid method that the aerodynamic flow fields in the near region around the sound source is solved by CFD and then the sound propagation is obtained by the wave equation. The finite volume method is used to solve the three dimensional incompressible Navier-Stokes equations, and the sound propagation is predicted using the Curle’s acoustic analogy. The predicted acoustic pressure is compared with measurement data reported by Brooks et al.. The effective angle of attack in the measurement has to be known for validation and is also discussed in this paper. The results show that the predicted frequency of a primary peak in the SPL spectrum is in good agreement with the measurement data. However, the simulated span length is 10% of the actual one and the sound source outside the computational domain needs to be corrected properly for more precise sound prediction.