In order to research the effect of combustion rate of the propellant on the operation process and the firing range of base bleed projectile, the flight ballistic of base bleed projectile was solved by using the computational aerodynamics coupled with particle trajectory.The changes of operation parameter, operation status, flow filed of base bleed projectile with time in the drag reduction stage were studied.The effect of combustion rate of propellant on the operation process and firing range of base bleed projectile were analyzed in detail.The simulation results are in good agreement with the target range test results of the standard base bleed projectile, indicating that the calculation model established is correct and reasonable.When the combustion rate adjustment coefficient changes from 0.8 to 1.2, the combustion time decreases from 36.4 s to 18.4 s, firing range decreases from 38.12 km to 36.21 km and the extended-range rate decreases from 33.32% to 26.64%.With the increasing of time, the base bleed parameters of the base bleed projectile with different combustion rate increase first and then decrease during the drag reduction period.The bleed mass flow rate of base bleed projectile with high combustion rate is larger than that of the base bleed projectile with low combustion rate, but there is no obvious increase of reduction drag effect.