Experimental and Computational Investigation of Divergent Thrust Losses In Rocket Nozzles

Abstract

The nozzle is a critical component of any rocket engine because it transforms high pressure and high temperature (with sluggish net velocity) within the combustion chamber into high velocity but low pressure. Individually, the molecules in the mixed propellants have rapid velocity in the combustion chamber, but directions are randomly pointing in all directions. A convergent-divergent nozzle, also known as a CD nozzle, is fashioned like a tube with two bulging ends and a thin part in the center. This structure/design provides the nozzle with a balanced shape. By turning the flow's heat energy into kinetic energy, the nozzle accelerates hot, pressured gas traveling past it in the axial (push) direction. Whereas the nozzle provides the acquired incremental thrust to the rocket engine, it also results in unwanted thrust losses. Out of which divergent losses in the divergent section are the primary foci of our research. Moreover, in this research paper, we produced verified results to reduce the thrust losses at the divergent sections of the nozzle by optimizing the nozzle with different half divergent angles.