Based on the Navier-Stokes equation and the turbulence model of single Spalart-Allmaras equation, the flow field of a low-drag hollow projectile was simulated numerically. The solution technology for above equations including the finite volume method for discretion of space terms, AUSM scheme was employed for the solution of convection terms and the adaptive mesh re-finement technology was used to improve the resolution for the shock wave capture. The complicated shock wave structures and the drag curves were obtained, furthermore, the flight characteristics of the hollow projectile with different Mach numbers and attack angles were discussed.