The invention discloses a rotary stamping compressed rotor plane cascade experimental system comprising an air supply system, a wind tunnel barrel, a Laval nozzle, a plane cascade experimental section, and an experimental test and data acquisition system. The plane cascade experimental section is composed of an upper cover plate, a lower end wall, a lower support plate, partition plates, a compression surface, a throat, a pressure expansion surface, a throttle valve, a throttle valve motor, a throttle valve frequency converter, and a rotatable platform. The plane cascade experimental section is provided with an odd number of air inlet flow paths which are partitioned by an even number of partition plates. The Laval nozzle is arranged before the plane cascade experimental section, high supersonic flow is achieved with low cost and low technical difficulty, and the inlet flow Mach number can be adjusted by replacing the Laval nozzle, so that rotary stamping compressed rotor plane cascade experimental study under different flow Mach numbers is realized. Moreover, rotary stamping compressed rotor plane cascade experimental study under different back pressures, different flow angles of attack and different partition top gaps can be carried out.