Abstract: A numerical investigation on aerodynamic characteristics of an X51Alike aircraft model, which was figured out based some published literatures, was carried out at angles of attack from -10°to +10°and flight Mach number 6. The basic aerodynamic characteristics such as the lift coefficient, drag coefficient and lift/drag ratio etc. were obtained and examined with available experimental data from public literatures. The applicability of the model as well as the influence of angle of attack upon aerodynamic flow field and performance was evaluated.