Abstract: China Aerodynamics Research and Development Center (CARDC) established a uniform large aspect ratio transport aircraft calibration model system for high and low speed wind tunnels to fulfill the data quality requirements of aircraft type development and CFD validation and confirmation. To acquire reliable wind tunnel data, CARDC tested the first self-developed transport calibration model CHN-T1 (1:6.4, 4.667m wing span) in FL-13 wind tunnel and DNW-LLF wind tunnel at chord Reynolds number from 1.4 to 2.5 million in FL-13 wind tunnel and from 1.4 to 3.2 million in DNW-LLF wind tunnel for the same configuration. CHN-T1 model was mounted on a TG1801A six-component strain-gauge internal main balance connected to the large angle of attack (AOA) support mechanism in FL-13 wind tunnel and on a W616 internal main balance connected to a sting support in DNW-LLF wind tunnel. Both of the force and moment data were obtained in both facilities. Tunnel to tunnel variations including repeatability, aerodynamic characteristics and Reynolds effect have been assessed. Results comparison shows that slop of lift curve (C_Lα) varies very little and drag coefficient (C_D) is of a difference of 0.0004 around the design point with Ma=0.78 and lift coefficient (C_L)=0.5. Test data indicates good agreement. Reynolds number effect on CHN-T1 calibration model aerodynamic characteristics follows the expected trends.