Abstract: Dynamic stall is a nonlinear and unsteady aerodynamic phenomenon prevalent in rotating machinery such as helicopters, wind turbines, and compressors, as well as in aircraft maneuvers involving high angles of attack and formation flight. This phenomenon encompasses flow separation, shear layer instability, and the formation and development of dynamic stall vortices, accompanied by pronounced aerodynamic hysteresis effects and substantial dynamic load variations. These characteristics often lead to operational challenges, including abrupt lift reduction, sharp increase in drag, and structural flutter. Since cutting-edge aerodynamic challenges including unsteady transition prediction, high angle of attack separation, and reliable dynamic stall simulation have not yet been solved, wind tunnel testing remains the primary approach for investigating dynamic stall characteristics and underlying flow mechanisms. This paper provides a systematic review of the advances in fundamental attributes of dynamic stall and wind tunnel experimental methodologies, with particular emphasis on pressure measurement techniques, transition detection methods, and high-resolution flow field visualization technologies. The findings highlight that high-precision and high-resolution experimental measurements are essential for capturing the flow characteristics during dynamic stall, while error correction techniques significantly enhance the reliability of experimental data. Furthermore, future research should prioritize the development of multi-physics coupled measurement technologies and integrate intelligent wind tunnel testing with machine learning approaches. Such advancements will enable comprehensive analysis of dynamic stall mechanisms and facilitate efficient aerodynamic design optimization and flow control strategies in aerospace and wind energy applications.