The rotating variant wing is an aerodynamic configuration of an intelligent loitering missile system. It has the advantages of compact structure, large body volume and high lift-drag ratio. This paper conducts aerodynamic computational analysis on the rotating variant wing configuration of intelligent loitering missile. Firstly, the aerodynamic configuration of the rotating variant wing is clarified and adopted by the intelligent loitering missile. Secondly, the grid for CFD calculation is completed, and the Reynolds-averaged Navier-Stokes (RANS) numerical method based the Meter k-ω SST (Shear Stress Transport) turbulence model is selected. And then, the lift-to-drag performance and pitching characteristics of the intelligent loitering missile are analyzed. Finally, the conclusion of aerodynamic analysis is given. The research results show that the rotating variant wing configuration of the intelligent loitering missile has good longitudinal static stability. Its maximum lift-to-drag ratio is 9.43 at subsonic, and the lift-to-drag ratio gradually decreases as Mach number increases. When Ma is greater than 0.95, the drag has a divergent trend. The rotating variant wing configuration is an aerodynamic configuration suitable for subsonic cruise and delivery of sub-sonic, transonic, supersonic.