The present invention provides a high-speed wind tunnel high-angle-of-
attack pitching dynamic stall test device. The device is driven by a motor, and the 
flywheel is driven to rotate through a 
belt drive wheel. The central axis of the 
flywheel drives a synchronous transmission gear set to transmit 
kinetic energy to the main drive.  The four-link 
motion system consists of the main 
drive wheel, the connecting rod and the rotating window, which realizes the conversion of the 
flywheel rotation into the reciprocating oscillation of the rotating window, and then drives the fixed aircraft model to achieve pitching motion at a large 
angle of attack.  The high-speed wind tunnel pitching dynamic stall test device with large 
angle of attack of the present invention overcomes the difficulties of strong vibration during operation of the existing high-speed wind tunnel, small space in the test section, low structural 
response frequency of the test section, and large 
environmental noise, etc., and can provide  The dynamic aerodynamic test results of the aircraft model under the conditions of large 
angle of attack (up to 75°), large amplitude (‑15°~75°), and 
high frequency (0~6Hz) are used for aerodynamic optimization design, flight quality evaluation, and control rate design  Provide key test basis.