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Rocket Propulsion Analysis Lite 1.1.4

Rocket Propulsion Analysis (RPA) is a multi-platform rocket engine analysis tool


Last Week downloads: 0
Total downloads: 167
  • Last Updated: Jan 25, 2011
  • License: Freeware Free
  • OS: Windows XP/2000/98
  • Requirements: No special requirements

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For Rocket Propulsion Analysis Lite 1.1.4Publisher's description


Rocket Propulsion Analysis Lite is a Photo & Image software developed by Alexander Ponomarenko. After our trial and test, the software is proved to be official, secure and free. Here is the official description for Rocket Propulsion Analysis Lite:

Edit By BS Editor: 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, 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.


* 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
* Etc
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