Mathematical modeling and numerical simulations for performance prediction in case of a liquid propelled rocket engine

The design and performance prediction of rocket engines require appropriate mathematical modeling for complex intricate phenomena; the main goals are optimized geometry and obtaining the best numerical accuracy. The algorithms and input data can be validated with numerical simulations, in experiment and comparison with available data from state of art survey. Relevant to this topic, can be approached investigations for complex and intricate phenomena, such as: propellant atomization, mixing, evaporation, chemical reaction, gas expansion, as well as effects (e.g. chemical reaction rates, and boundary-layer and streamline and velocity-vector divergence in the converging and diverging nozzles) intended to a more accurate description of real phenomena. This paper presents an exhaustive study, based on iterative calculations for a liquid propelled rocket engine, with optimized performances and improved geometry. The results of our research (optimized LPRE) is driven environment friendly due to the selection of fuels: Kerosene (RP-1) and Liquid Oxygene (LOX).