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.