| Feature |
Standard Edition v.2.x |
Standard Edition v.1.x |
Lite Edition |
| Calculation of heat transfer rate distribution (convection and radiation) with or without boundary layer coolant and/or thermal barrier coating layer |
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| Film cooling analysis |
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| Radiation cooling analysis |
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Regenerative cooling analysis:
- coaxial shell jacket
- tubular jacket
- jacket with milled channels
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| Thermal analysis of thrust chambers with combined cooling (radiation + film + regenerative) |
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| Estimation of hydraulic losses in the cooling passages |
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| Estimation of friction thrust loss |
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| Estimation of divergence thrust loss for nozzle with truncated ideal nozzle contour (TIC) |
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| Calculation of thermal transport properties |
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| Scripting module to solve user's own problems, extending standard capabilities of the program |
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| Propellant analysis tool to evaluate different propellant compositions,
with stepwise replacement of one component with another one |
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| 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 |
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| 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 |
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| Producing publication-quality plots (in raster or vector format) |
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| Output of results to PDF or ODF format |
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| Analysis of monopropellant and bipropellant rocket engines |
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| Analysis of rocket propulsion engines with an arbitrary set of propellant components (multipropellant systems)
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| Robust, proven and industry-accepted Gibbs free energy minimization approach is used to
obtain the combustion composition |
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| Calculation of performance for a finite- and infinite-area combustion chambers |
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| Analysis of nozzle flows with shifting and frozen chemical equilibrium |
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| Calculation of thrust coefficient, characteristic velocity and specific impulse
(sea level, optimum expansion, vacuum) |
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| Optimisation of propellant components mixture ratio for maximum specific impulse of bipropellant systems |
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| Altitude performance analysis |
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| Analysis of nozzle performance with respect to overexpansion and flow separation |
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| Throttled engine performance analysis |
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| Estimation of test (delivered) nozzle performance |
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| Expandable thermodynamic data library mainly based on
NASA Glenn thermodynamic database
includes data for numerous combustion product species, as well as data for such propellant components as
hydrogen, oxygen, RP-1, RG-1, Synthine, methane, propane, hydrogen peroxide, MMH, and many other |
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| Built-in species database editor: the users can incorporate into the thermodynamic data
library his/her own chemical species, or species obtained from
third parties |
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| Tool for import components from PROPEP or CEA2 species databases |
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| Nested analysis tool to evaluate the performance under different conditions,
stepping of up to four independent variables (component ratio, chamber pressure,
nozzle inlet conditions, nozzle exit conditions) |
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| Multi-platform graphical user interface for Microsoft® Windows™
(both x86 and x86-64), as well as for Apple® Mac OS X and Linux |
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Supported units for input data:
- pressure:
MPa, Pa, atm, bar, psia, kg/cm2
- mass flux:
kg/(m2·s), lbm/(ft2·s)
- temperature:
K, R, C, F
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| Results output in SI or U.S. customary units |
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| Output of results to Plain Text or HTML format |
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| Graphical output of results of altitude and throttled engine performance analysis |
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| Printing results of analysis |
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| Two modes for comfortable work: Express Analysis and Extended Analysis |
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