The invention relates to a continuous transonic wind tunnel airfoil dynamic experimental amplitude angle adjustment mechanism which is based on a crank-rocker mechanism and realizes accurate adjustment of an amplitude angle of an airfoil model during pitching oscillation by adjusting the position of a slider and the length of a connection rod. A driving motor at the top of a wind tunnel provides apower source for the whole device, so that a rocker arm is driven to oscillate in a pitching way through the connection rod while the crank device of the adjusting mechanism does circular motion around a motor shaft; the rocker arm is connected with an oscillating shaft, further driving the oscillating shaft to carry out periodic pitching oscillation along the axial direction; the airfoil model used in the experiment penetrates through a dynamic experiment dedicated rotating window through a lug and is connected with the oscillating shaft; finally, it is realized that the airfoil model does the periodic pitching oscillation motion at a specific amplitude angle. The continuous transonic wind tunnel airfoil dynamic experimental amplitude angle adjustment mechanism in the invention can provide accurate and reliable experimental data for the aerodynamic performance evaluation of the airfoil of the high mobility aircraft under different amplitude angle conditions and provide a basis for optimized design thereof.