The aerodynamic design procedure of a large-scale aircraft noise suppression facility has been developed. Flow quality required for the engine intake was determined through basic experimentation. Aerodynamic design of the facility has been performed by wind tunnel experiment and CFD. An important relationship between the length of the facility and the engine intake flow quality was found. The operation envelope of the designed facility was estimated. Then, the aerodynamic characteristics of an actual large-scale aircraft noise suppression facility, constructed based on the new design procedure, was measured. The obtained flow field showed good agreement with CFD results, and the effectiveness of the design procedure based on CFD and wind tunnel experiment has been confirmed. The engine operations were satisfactory under various wind conditions. Furthermore, the data under commercial operations thereafter were collected and analyzed. As the result, the aerodynamic design procedure has been successfully validated.