Flow and motion of condensed-phase particles in the prenozzle space of solid-propellant rocket motors.

The flow of an inviscid liquid containing condensed-phase particles around the recessed nozzle of the solidpropellant rocket motor has been considered. To take into account the complex geometry of the prenozzle space of the rocket motor, the equations describing the liquid flow were written in a curvilinear coordinate system. The paths of solid particles were calculated in the known liquid flow field. The quality criteria of the meshes constructed with the use of different approaches have been compared. The results of the calculations permit determining the limit path of particles dividing the flow region into two subregions, one of which is occupied by particles and the other is free from condensed-phase particles. [ABSTRACT FROM AUTHOR]