Abstract: At the FL−13 wind tunnel of China Aerodynamics Research and Development Center, based on the 4 meters diameter rotor and fuselage and tail rotor combination model test rig, a helicopter full aircraft combination model wind tunnel test technology was constructed, which achieved relatively convenient conversion of thrust and pull type tail rotor layout, developed a balancing strategy under the full aircraft combination model state, provided test methods, standardized test procedures, and formed a complete helicopter full air-craft combination model wind tunnel test capability, provided technical support for conducting experimental research on the comprehensive aerodynamic performance and interference characteristics of the entire helicopter. By conducting wind tunnel tests on a 4 meters diameter rotor and fuselage and tail rotor combination model, the aerodynamic characteristics of rotor, fuselage, tail rotor and other components of a certain helicopter in side flight state, as well as the aerodynamic interference characteristics between rotor, fuselage, tail rotor and other components in forward flight state, were obtained. This provides a data basis for verifying numerical simulation methods and improving the overall aerodynamic layout.