The report describes a numerical model and presents equations used for the combustion equilibrium and performance calculations. Results obtained from implementing these equations will be compared with results from equilibrium code CEA2.

The report describes a numerical model of thermal analysis of cooled combustion chambers and nozzles, implemented as a Thermal Analysis Module for RPA.

This report describes a numerical models and computation techniques implemented in RPA to estimate the delivered performance of thrust chambers.

This report describes a numerical model used in RPA to estimate the mass of the engine.

This conference paper presents the Rocket Propulsion Analysis tool (RPA) - a multi-platform computational package intended for use in the conceptual and preliminary design of liquid-propellantrocket engines.
A description of the components and the most important aspects of the physical modeling is included. It provides details on the following modules: thrust chamber performance analysis, combustion chamber sizing and nozzle contour design, thrust chamber thermal analysis, engine cycle analysis and weight estimation. Physical models implemented in RPA enable the analysis of rocket engines with accuracy sufficient for conceptual and preliminary design studies.
All modules are integrated into executable with user-friendly graphical user interface. Development tools (set of libraries and documented API) are available, allowing the user to create various custom solutions, including simple scripts written in JavaScript, programs written in Python, or complex applications written in C++.

Conference presentation.

Presentation given at ESA/ESTEC.