Development and Application of a Comprehensive Analysis of Liquid-Rocket Combustion

A comprehensive method for analyzing liquid-rocket engine combustion is introduced, which utilizes and unifies the results of analytical and experimental research in the fields of liquid-propellant injection and combustion. A system of 3-dimensiorial, time-dependent, nonlinear-conservation equations is derived and the necessary expressions for bipropellant spray-mass distribution, drop size, drop velocities, spray evaporation, and interphase drag are presented. Specialized application of the general model to the analysis of ablative-chamber compatibility is summarized and illustrated.