Analysis of aluminum particle combustion in a downward burning solid rocket propellant

In this study, aluminum particle burn in a gap created between a downward facing combusting propellant surface and an upward facing inert surface was modeled with sensitivity testing on propellant surface velocity, propellant surface temperature, propellant surface radiation temperature, parcel count, particle diameter, turbulent Prandtl number and turbulent Schmidt number. Decreasing the turbulent Prandtl and turbulent Schmidt number appeared to have little effect on the maximum temperature. Increasing/decreasing the velocity of the propellant surface and propellant surface temperature showed greater sensitivity on the plume temperature. Perturbation of the propellant surface temperature had the greatest influence on the maximum gas temperature. By increasing and decreasing the surface temperature by ten percent of its original value, a temperature difference of 265.4 K and 248.7 K were observed, respectively.