Numerical simulations for the aerodynamic characteristics of near space hypersonic projectile have been computed using the Spalart-Allmaras (SA) turbulence model and thermally perfect model, a time-dependent, finite-volume numerical method and AUSM+ scheme are adopted to solve the three dimensional Navier-Stokes equation. Numerical solutions of hypersonic projectile flow-field with attack angle are obtained, and the numerical results can be used in the further study of the near space hypersonic projectile and missile.