Abstract: In order to fully study the dynamic stall of the helicopter rotor, a pitching and plunging dynamic test device is developed in the FL-11 wind tunnel. Firstly, the paper introduces the design of its mechanical structure, and the statics and model analysis of the mechanical frame and the moving base is conducted through the finite element analysis. Then, the pitching and plunging oscillatory motion of the device is achieved by the multi-motor synchronous driving control, and the control precision is guaranteed through the motion control system based on SIMOTION D and S120. Finally, the synchronous control technology based on the locked gain compensation algorithm of the gantry axis is used to improve the synchronous precision of the motor, and the stepless adjustment of the amplitude and frequency is realized by the electronic CAM technology. The results show that the device can implement the pitching motion and the plunging motion separately or in conjunction, the maximum amplitude of the pitching oscillation is 15°, the highest frequency is 5 Hz, the maximum amplitude of the plunging oscillation is 130 mm, the highest frequency is 5 Hz, and the angle and displacement accuracy is 3′ and 1 mm respectively. The device has been successfully applied to the aerodynamic characteristics wind tunnel test of CRA309 airfoil, which provides a test platform for in-depth study of dynamic stall characteristics.