Portable Rocket Propulsion Analysis Standard

Name: Portable Rocket Propulsion Analysis Standard
Works on: windows

Windows 2000 and above

Version: 2.2
Last Updated: 05 Apr 2017
Release: 10 May 2015
Category: Portable > Other Portable Applications

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Portable Rocket Propulsion Analysis Standard Tags

engine analysis engine performance analyzer thermodynamic analysis engine performance engine rocket Thermodynamics

Portable Rocket Propulsion Analysis Standard Details

Rating: 2.652173913 out of 5 based on 23 user ratings

Publisher Website: External Link
Downloads: 1365
License: Demo / Trial Version

Portable Rocket Propulsion Analysis Standard is a demo software by Alexander Ponomarenko and works on Windows 10, Windows 8.1, Windows 8, Windows 7, Windows XP, Windows 2000, Windows 2003, Windows 2008, Windows Vista, Windows 2012.
You can download Portable Rocket Propulsion Analysis Standard which is 14.03 MB in size and belongs to the software category Other Portable Applications.
Portable Rocket Propulsion Analysis Standard was released on 2015-05-10 and last updated on our database on 2017-04-05 and is currently at version 2.2.
We also have Portable Rocket Propulsion Analysis Standard 64bit version which is 15.04 MB in size and will work on x64 computers.

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Portable Rocket Propulsion Analysis Standard Description

Staged Combustion cycle (SG), Full Flow Staged Combustion cycle (FFSG) and Gas Generator cycle (GG) engine cycle analysis
Estimation of engine performance for Gas Generator cycle
Estimation of engine dry weight
Propellant analysis tool to evaluate different propellant compositions, with stepwise replacement of one component with another one
Film cooling analysis
Radiation cooling analysis
Estimation of test (delivered) nozzle performance
Throttled engine performance analysis
Designing parabolic nozzle contour or truncated ideal nozzle contour (TIC) using two-dimensional (axisymmetric) method of characteristics, with capability to export the resulting contour to DXF file
Determination of combustion chamber size for given thrust, propellant mass flow rate, or throat diameter, with capability to export the resulting contour to DXF or ASCII file
Optimization of propellant components mixture ratio for maximum specific impulse of bipropellant systems
Altitude performance analysis