The wind tunnel dynamic derivative data are the essential key parameters when analyzing the stability of the aircraft and designing the control law. In order to solve the problem that the accuracy of dynamic derivative data in wind tunnel which are affected by the low Reynolds number due to small model size and low wind speed, and satisfy the urgent need of the high-accuracy dynamic derivative test data for the development of high-aspect ratio aircraft, a dynamic derivative test system with 5 kinds of oscillation capabilities is developed by the AVIC Aerodynamics Research Institute based on the large-scale low-speed wind tunnel of 8 m × 6 m. This test system uses the servo hydraulic motor and servo hydraulic cylinder as the driving components of the oscillation motion, and directly generates arbitrary waveform forced motion through the control of the servo valve, which has the characteristics of small motion transmission gap, high motion control precision and high system automation. The system can realize the dynamic derivative test model at the maximum wingspan of 4m, the maximum wind speed at 60 m/s, the angle of attack at − 10° ~ 40°, and the sideslip Angle at − 30° ~ 30°. The dynamic derivative verification test of this system is carried out by using a high span chord ratio dynamic standard model with 3m wingspan length. The results show that the dynamic derivative test data obtained is reasonable and the data accuracy is better than 4% which can provide dynamic derivative test platform support for the development of large wingspan military and civilian aircraft in China.