Análise da seção divergente de bocal supersônico utilizando o método das características

Abstract

Rocket engines are essential for space exploration. With technological advances, the optimization of these engine components has become increasingly crucial.This study proposes the use of the method of characteristics to design the divergent section of a liquid-propellant supersonic rocket engine nozzle. A Python algorithm will be implemented to determine the optimal nozzle geometry based on the following input parameters: Mach number at the nozzle exit and the number of characteristic lines. Other necessary values, such as throat radius and properties in the combustion chamber, will be modeled based on data from SpaceX’s Merlin 1D engine. In this context, the variation of the Mach number at the nozzle exit and the adiabatic expansion coefficient will be investigated to understand the implications of these variations on operating conditions and rocket performance, with the aim of improving engine design and optimization. To ensure efficient flow, the Method of Characteristics will be used to obtain a long nozzle. The determination of the optimal length of the truncated nozzle will be carried out, considering the relationship between mass savings and engine efficiency. Based on the expected results, this study aims to contribute to the development of more efficient rocket engines by providing a reliable design method adaptable to the specific needs of each application.