Blade missile， characterized by a small killing range and low damage effect， is suitable for special operation missions. In consideration of the effects of spin and flow velocity on the aerodynamic force of blade missiles in both deployed and retracted states， the variation of aerodynamic parameters during transonic flight was investigated. The sliding grid technique was applied to divide the flow field into a stationary region and a rotating region surrounding the missile. The ICEM CFD preprocessing software was applied to generate seven million grids by a multi-block splicing method， with a turbulence model and boundary conditions set. A simulation model of the blade missile was established， and the grid convergence and time step independence were verified. The aerodynamic characteristics of the blade missile during deployment and retraction were investigated， and the pressure distribution law of the external flow field at different positions of the missile was calculated under different Mach numbers and spin speeds. The calculation results show that the aerodynamic parameters increase first and then decrease with velocity， and they reach a maximum value at a Mach number of around 1.2， which has certain guiding significance for the development of blade missiles.