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Rocket Propulsion Analysis Standard

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Rocket Propulsion Analysis Standard screenshot
Name: Rocket Propulsion Analysis Standard
Works on: windowsWindows 2000 and above
Version: 2.2
Last Updated: 05 Apr 2017
Release: 09 May 2015
Category: Science CAD
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2194 downloads
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details

Rocket Propulsion Analysis Standard Details

Works on: Windows 10 | Windows 8.1 | Windows 8 | Windows 7 | Windows XP | Windows 2000 | Windows 2003 | Windows 2008 | Windows Vista | Windows 2012
File Format: exe

SHA1 Hash 32bit version: 3725ea0e744ce9a43baa11c3ec992f7bf0ec1278
Size 32bit version: 16.81 MB

SHA1 Hash 64bit version: 2ce9be3e8f9dea39166749c2168da2e15f83ab58
Size 64bit version: 18.16 MB

Rating: 2.434782608 out of 5 based on 23 user ratings
Publisher Website: External Link
Downloads: 2194
License: Demo / Trial Version
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 Rocket Propulsion Analysis Standard which is 16.81 MB in size and belongs to the software category Science CAD.
Rocket Propulsion Analysis Standard was released on 2015-05-09 and last updated on our database on 2017-04-05 and is currently at version 2.2.
We also have Rocket Propulsion Analysis Standard 64bit version which is 18.16 MB in size and will work on x64 computers.
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features

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
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Where to buy?

Last updated price and discount information 6 years agoupdate now
$325.00Click the link to buy
screenshots

Rocket Propulsion Analysis Standard Screenshots

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