Airfoil dynamic stall refers to a strong nonlinear and unsteady flow phenomenon caused by the large-scale separation of the surrounding surface layer when the local angle of attack of the wing or blade changes periodically or sharply.The dynamic stall vortex breaks away from the airfoil. When the trailing edge flows downstream， it will cause stall and flutter problems with a sharp drop in lift and a rapid increase in drag. Based on the two-degree-of-freedom dynamic test device of the rotor airfoil and the high-frequency and high-speed oscillation test device， the typical rotor airfoil is used as the research object， the experimental research on dynamic stall plasma flow control of airfoil is carried out in FL-11 and FL-20 wind tunnels by using nanosecond pulse excitation power supply and dielectric barrier discharge plasma exciter. The maximum Reynolds number in the test exceeds 1.7×10⁶， and the maximum oscillation frequency of the model exceeds 10 Hz. The test results show that the plasma aerodynamic excitation can effectively control the dynamic stall of the airfoil， improve the average aerodynamic force， reduce the negative peak of the pitching moment and the hysteresis area of the aerodynamic force/torque with the angle of attack.