The aim of this research is to examine the effects of propellant properties such as: combustion temperature, propellant density, characteristic velocity, reference burning rate and burning rate pressure exponent on internal ballistic performance of solid rocket motors. A zero dimensional internal ballistic solver is developed and internal ballistic performance analyses of solid rocket motors having slotted cross section are performed. Thus, different internal ballistic results such as maximum combustion pressure, burning time, specific impulse and total impulse are determined. Finally, variation of these response variables according to solid propellant properties are determined constructing different response surfaces. Graphical results represented in this work makes easier to select solid propellants for a certain kind of geometrical configuration.