Composite modified double-base propellants (CMDB) are characterized with high energy output, wide range of burning rates, as well as enhanced ballistic performance. Recently, much attention has been directed toward the development CMDB. One of the main approaches for the achievement of CMDB includes the integration of an effective oxidizers and fuels, in an attempt to maximize the output heat. This study reports on the effects of potential oxidizers including potassium perchlorate and ammonium perchlorate on the ballistic performance, particularly burning rate, of double base propellant. The ballistic parameters of several CMDB formulations were investigated using a chemical equilibrium computer program named ICT Thermodynamic Code (Institute of Chemical Technology in Germany, virgin 2008). Theoretically, there was an increase in specific impulse with the increase of potassium perchlorate (KP) and ammonium perchlorate (AP) content up to 20 wt.%. CMDB formulations based on different wt. % of KP and AP up to 10 wt. % were manufactured by extrusion process. The practical ballistic performance was evaluated using static test (small scale one inch rocket motor). The two oxidizers exhibited controversy effect. The burning rate was increased by 22 % with the addition of 10 wt. % KP; whereas the characteristic exhaust velocity (C*) was increased by 5.3 % with the addition of 10 wt. % AP. This paper might open the route for the manufacture of CMDB with tailored enhanced performance in terms of specific impulse and burning rate.