Abstract
Hybrid rocket combustion has important effects on rocket performance. The solid fuel regression rate is an important quantity in the hybrid rocket operation. In the past years, experimental and analytical investigations have been conducted to find correlations to correctly predict the regression rate. Numerical computations are becoming more important in the estimation of the characteristic parameters of such a complex combustion that embraces many different phenomena. This study predicts the regression rate of the Hydroxyl-Terminated Poly-Butadiene/Gaseous Oxygen formulation and its sensitivities to some operating parameters, such as combustion chamber pressure, oxygen inlet temperature, and mass flow rate. Furthermore, an analysis of other variables is used to explain the experimentally observed regression rate behavior. Particular emphasis is placed on the effect of the oxygen between the flame and the surface, which is considered responsible for the pyrolysis process enhancement.
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