The invention discloses a helicopter combined model wind tunnel test device with an independent tail rotor device. The device comprises a fuselage model, a fuselage model balance, a main rotor, a mainrotor driving system, a variable pitch mechanism, a main rotor balance, a torque balance, a tail rotor and a support system. The fuselage model is internally provided with a tail rotor balance, a tail rotor motor and a tail rotor transmission mechanism; a first rigid bottom plate and a base are arranged in the fuselage model, the tail rotor motor and the tail rotor transmission mechanism are connected with the floating end of the tail rotor balance through the base, and the tail rotor is fixedly installed on an output shaft of the tail rotor transmission mechanism and keeps the spatial position of the fuselage model unchanged all the time. The tail rotor motor and the tail rotor transmission mechanism are not in contact with other parts; the support system drives the fuselage model, the main rotor and the tail rotor to change positions and postures at the same time. By adopting the helicopter combined model wind tunnel test device with the independent tail rotor device, the positionsand the postures of the fuselage model, the main rotor and the tail rotor can be changed simultaneously in the test process.