Abstract
Abstract : A theoretical analysis of the erosive burning of solid propellants is presented using a reacting turbulent boundary layer approach. The turbulent field is modeled using the second-order closure technique and a single-step gas-phase reaction is assumed for the combustion of a homogeneous propellant. The calculated results agree with the generally observed erosive burning trends of threshold velocity, nonlinear recession-ratio velocity dependence, pressure dependence, and normal burning rate sensitivity. For constant external velocity boundary layers, the results show a decrease in burning rate along the propellant surface, which also has been observed experimentally. Examination of calculated profiles of temperature and turbulent correlations in the boundary layer reveals that erosive burning is predominantly caused by flame zone broadening due to the diffusive effects of turbulence. (Author)
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