Research on aerodynamic optimization of hypersonic missiles

Abstract To investigate the impact of different components on the aerodynamic characteristics of hypersonic missiles and missiles’optimization, a numerical simulation model of the typical hypersonic missile aerodynamic optimization was developed based on Ansys/Fluent. Based on this foundation, the missile was three-dimensionally modeled using Solidworks software. Detailed aerodynamic performance analysis was conducted on its head, tail, and canard configuration, which included key aerodynamic performance indicators such as drag coefficient and lift-drag ratio. The research findings indicate that the aerodynamic performance of the missile head design significantly affects the missile structure under investigation. Appropriate increase in the number of tail fins can effectively enhance the overall aerodynamic performance of the missile, however, if the number exceeds a certain limit, it may exert a detrimental impact on performance. In addition, at high attack angles, the use of canard configuration can significantly increase the missile’s lift coefficient and stability.