Abstract: The typical near space vehicle configuration causes many problems on aerodynamic characteristics especially the stability of the vehicle, which threatens the flight security. Therefore, the research was performed on an HTV-2 like configuration for hypersonic characteristics. The wind tunnel test and computational data were given and compared in this paper with a great coherence, which shows this vehicle could meet the design requirements with the fact that the vehicle has a relatively high ratio of lift to drag and owns satisfied static stability. For further study, the aerodynamic characteristics were also evaluated at broad speed and altitude range to study the regulation at different flight conditions. Besides, the wind tunnel test was conducted to study the effects of two-degree coupling motion on the dynamic characteristics. The results show that the forced pitching motion will cause oscillatory motion in rolling direction, although the vehicle is of one-degree dynamic stability.