Fan is one of the main noise sources of the aircraft engine, mainly including discrete tone and broadband noise. With the increasing maturity of discrete noise researches, broadband noise has become increasingly prominent. In this study, the synthetic eddy method (SEM) coupled with the radiation non-reflective boundary condition is implemented to a high order computational aeroacoustics(CAA) solver. The synthetic eddy method is validated with simulation of the decay of isotropic turbulence. The turbulence generated with SEM is imposed in the boundary upstream. The velocities spectra at different locations downstream are presented and compared with the experimental data. The developed code is then applied to computed the gust/airfoil interaction benchmark problem to validate the non-reflective boundary condition. The numerical results are compared with the reference data by other researchers, and a good agreement is obtained. Finally the broadband noise generated from the interaction of turbulence and NACA0012 airfoil is simulated with the developed code. The far field noise spectra are compared with the experimental data and reference computational results by other researchers.
