Abstract: Control surface buzz of the aircraft is an aeroelastic instability phenomenon during the transonic flight. The occurrence of buzz can reduce the efficiency of aircraft control surfaces, and even cause disastrous flight accidents. Therefore, the buzz phenomenon is another difficult aeroelastic problem that the aircraft design department focuses on in addition to the flutter. Control surface buzz is related to the interaction between the shock wave and the boundary layer, and there is no accurate calculation method to obtain the buzz characteristics, thus the wind tunnel test is usually used to acquire relevant data. The buzz wind tunnel test can be used to reproduce the buzz phenomenon and study its characteristics, which is the most effective method to verify the anti-buzz design in the aircraft development stage. In the present study, we review previous studies of buzz wind tunnel tests. The occurrence mechanism, triggering conditions and control surface buzz classification are sorted out. Feasible suggestions for suitable wind tunnel selection, model design and test methods of buzz wind tunnel test are provided, and effective methods to distinguish the buzz phenomenon during the flutter test are discussed. The follow-up work is presented in the end.