Computational fluid dynamics analyses are performed for situations of wind tunnel testing with various aircraft model geometries, angles of attack, and wind tunnel test section sizes. To enhance the efficiency of workflow, the geometry modeling, mesh generation, and analysis processes are automated. Wall interference correction factors(△α, ε) are obtained by using the resulting pressure coefficient along the test section wall and the concept of the wall pressure measurement method. The wall interference effects are identified and confirmed from the comparison of aerodynamic coefficients and analysis of computed correction factors. The origin of the wall interference is also investigated by flow field analysis. By confirming well-known characteristics from the obtained results, the reliability and validity of the established method for the obtaining the correction factors are confirmed.