A parametric model for thrust chamber preliminary design

摘要

This paper describes the elements of a parametric model designed to be used in the preliminary design of certain aspects of a liquid propellant thrust chamber. Starting with a set of parameters defined by the final user, this model delivers engine performance, combustion chamber and nozzle main dimensions with accuracy level acceptable for the conceptual design phase. Good correlation was found between actual engine dimensions and results obtained with the application of the parametric model herein described.