Numerical analysis of aerodynamics for missile with control-flaps

The simulation of the non-viscous problems of missile with control-flaps is presented in this paper. It is very difficult to simulate this configuration that have a very narrow gap between missile body and control-flap. To solve Euler equations for the complex body in better quality grid and high efficiency, hybrid grid technique that combine the structure grid with unstructured grid is presented. This grid is easier to fit for the configuration. The results show the agreement of present with wind tunnel test. Finally, a great amount of results of two different configurations are given. Via sufficient validation of the reliability of the calculation results, the aerodynamic performance of missile with flaps are analyzed, especially the static stability and trimming characteristics are discussed.