Internal Flow of a Rocket Engine Nozzle Calculated Through One-Dimensional Equilibrium

Modeling of the internal flow of a nozzle is a vital step in the design of a rocket engine. This study focuses on providing an in-depth examination of a thermochemical rocket engine’s operation through chemical equilibrium. The computation extends to cover both gaseous and condensed species, as well as phase transitions, offering a comprehensive understanding of the engine’s behavior. Notably, this research introduces the ability to freeze the composition at any chosen point within the nozzle, allowing for tailored modeling to specific engine conditions and enhancing its versatility as a tool for analysis and design. Moreover, the study takes an additional step by calculating the transport properties along the nozzle. Special note is made of the difference between equilibrium and frozen variables. By integrating equilibrium composition, condensed species, and transport properties, this research exemplifies a holistic approach to analyzing and optimizing the performance of thermochemical rocket engines, with several illustrative examples showcasing the capabilities of the program.