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.