Aiming at improving the range of wingbody combination aircraft at hypersonic flow conditions, the aerodynamic characteristics and wing efficiency of morphing tactical missile with different deformation modes at Mach number from 3 to 8 were studied. The NavierStokes equations were used to simulate the flow field, and the lifttodrag ratio, wing efficiency, stability and controllability of different deformation modes as telescopic, variable sweep and twodimensional folding were compared. Results show that under the condition of supersonic and hypersonic flow, the variable sweep wing mode improves the lifttodrag ratio significantly, and at the same time, it has excellent wing efficiency and stability and controllability. The mode performs best at the Mach number from 3 to 8. The conclusion can offer some valuable guidance to the research and application of hypersonic morphing aircraft aerodynamic configuration.