Abstract: The perforated test section of the 2.4 m×2.4 m injection driven transonic wind tunnel is redesigned so as to study the aerodynamic force of advanced aircraft. A scaled experimental research of the special perforated wall test section is conducted in the 0.24 m×0.20 m transonic wind tunnel (the pilot wind tunnel of the 2.4 m×2.4 m transonic wind tunnel). The experimental study has demonstrated that the project is feasible, and the flow quality of the flow field in the special perforated wall test section reaches the required specification. Influences of the diffuse angle in the test section, the open width of the mainstream ejected slot and the porosity of the perforated wall are also investigated. The results have been used to design the perforated test section of the 2.4 m×2.4 m transonic wind tunnel. The calibration parameters for the future perforated test section flow field calibration in this tunnel are also provided.