Analysis of aerodynamic characteristics of a modular assembled missile with canard rudder and arc tail

A modular assembled missile is designed recently. We can assemble different cabins just before launching to meet different requirements, and in this paper we choose one of the combinations of the cabins for analysis. Firstly, we use the commercial software Fluent to simulate the aerodynamic of the missile with arc tail and canard rudder in the high maneuvering state at different attack angles and different flying Mach number. Next, by changing the boundary conditions of simulation, the variation law of the lift coefficient, the drag coefficient and the pitch moment coefficient with the changing flight velocity of the missile module is obtained. In the subsonic and supersonic state, pressure cloud of the missile and the surrounding were both observed, then we compare them to verify the credibility of the simulation. At last we make conclusions about the shortcoming and advantages of the missile's shape, and introduce our future works.