This study considers investigation of combustion phenomena in a Solid Propellant Rocket Motor (SPRM).Gas dynamic in combustion chamber and effluent nozzle has been studied by solving governing equations (mass, energy, and momentum balances). In the modeling, spread of flame and variation of mass added from propellant surface into the gas stream are considered. The governing equations, which were in Euler form, were solved numerically by applying Modified Mac-Carmak method. Pressure, temperature and velocity distributions were found as a function of time and axial distance. The results were validated by experimental data of a typical rocket motor. Effects of various factors on combustion were evaluated. The proposed model can be easily modified and used for other solid propellants even with low aluminum content.

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