Rocket Propulsion Analysis Lite 1.2.9

Rocket Propulsion Analysis (RPA) is a multi-platform rocket engine analysis tool for rocketry professionals, scientists, students and amateurs.

For many years rocketry scientists, students and amateurs were using command-line MS-DOS or UNIX programs to calculate the performance of the rocket engines. While the accuracy of the old programs is still sufficient for many cases, the old-fashioned interface has poor usability, whereas the lack or absence of active development makes it difficult to satisfy new user requirements.

With release of the RPA Lite Edition, software.lpre.de offers the modern rocket engines analysis tool and promises continuous further development of the program.

RPA is an easy-to-use multi-platform tool for the performance prediction of rocket engines. It features an intuitive graphical user interface with convenient grouping the input parameters and analysis results.

RPA utilizes an expandable chemical species library based on NASA Glenn thermodynamic database and Gurvich thermodynamic database, that includes data for numerous fuels and oxidizers, such as liquid hydrogen and oxygen, kerosene, hydrogen peroxide, MMH, and many others. With embedded species editor, the users may also easily define new propellant components, or import components from PROPEP or CEA2 species databases.

By providing a few engine parameters such as combustion chamber pressure, used propellant components, and nozzle parameters, the program obtains chemical equilibrium composition of combustion products, determines its thermodynamic properties, and predicts the theoretical rocket performance. The results of calculation can also be used to design combustion chambers, gas generators and preburners of the liquid propellant rocket engines.

Main Features:

Robust, proven and industry-accepted Gibbs free energy minimization approach is used to obtain the combustion composition
Analysis of nozzle flows with shifting and frozen chemical equilibrium
Optimisation of propellant components mixture ratio for maximum specific impulse of bipropellant systems
Altitude performance analysis
Analysis of nozzle performance with respect to overexpansion and flow separation
Throttled engine performance analysis
Estimation of test (actual) nozzle performance
Nested analysis, stepping of up to four independent variables (component ratio, chamber pressure, nozzle inlet conditions, nozzle exit conditions)
Multi-platform graphical user interface for Microsoft® Windows™ (both x86 and x86-64), as well as for Apple® Mac OS X and Linux
Embedded species database editor

Release notes:

New Release
Mistake is fixed in estimation of chamber performance with flow separation in the nozzle
[ Rocket Propulsion Analysis Lite full changelog ]