A theory for momentum, energy, and mass transport in supersonic spray combustion

This paper summarizes the various models that the author has implemented, or intends to implement, for his investigations on supersonic spray combustion. The application of interest is the scramjet or rotating denotation engines in propulsion. However, a large part of the work on the fluid dynamic forces within the framework of the point-particle Eulerian/Lagrangian models for two-phase flows under supersonic conditions comes from the studies on explosives, where pressures are in the gigapascals. However, the pressures in the applications of interest to the author are of the order of unity. Therefore, some caution is required when interpreting some of the models presented in this work. The author’s position regarding the modeling of combustion in two-phase supersonic flows is that drop breakup should be an implicit component of the reactive flow analysis, so that the frequent practice in low-Mach number two-phase flows, of assuming purely spherical particles, may not at all be appropriate.