Aerodynamic study of theater ballistic missile target

This paper presents an aerodynamic study of “ × − + ” finned configurations for theater ballistic missile target (TBMT) which plays a key role to evaluate the Missile Defence System. The semi-empirical method (MISSILE DATCOM) and CFD method were selected to calculate the aerodynamic coefficients and flowfield for multiple sub-models. A wind tunnel experiment was conducted to explore the aerodynamic characteristics of this TBMT model in supersonic condition. Both computational methods are capable of predicting the aerodynamic coefficients of TBMT. The experimental results also showed that the “all stages” modelʼs pressure center only had small changes when α is increasing and the TBMTʼs maneuverability would increase after the first separation. The flowfield visualizations showed that the front finʼs trailing vortices had no interference with tail fins in small angle of attack condition. The “ × − + ” finned aerodynamic configuration can meet the need for high stability to lower the cost of the guidance and control system in the TBMT.