​In the design of a Solid Rocket Motor (SRM), and more in detail of the combustion chamber, some specific problems can be afforded by means of computational fluid dynamics tools. Among the others, the following  problems are particularly important: a) prediction of thermal loads on the internal wall of the chamber; b) pressure oscillations, due to hydrodynamic phenomena  and to the combustion. The latter phenomenon is particularly important since it can cause serious damages to the chamber and dangerous thrust oscillations. CFD can be used to analyse in detail both these problems, obtaining useful information in the design phase, provided that a proper confidence level can be assured, only achievable through a systematic comparison with the available experimental data. Actually, only a sufficient experience and confidence in the numerical results accuracy can allow the reduction of safety margins, with consequent decrease of weight. The goal of this project is therefore to identify a state of the art methodology to predict heat fluxes and pressure oscillation inside a SRM and to validate it with respect to available experimental data.