RPA Features

Feature Standard Edition v.2.x Standard Edition v.1.x Lite Edition v.1.x
Engine cycle analysis:
  • Staged Combustion cycle (SG)
  • Full Flow Staged Combustion cycle (FFSG)
  • Gas Generator cycle (GG)
Estimation of engine performance for Gas Generator cycle
Estimation of engine dry weigth
Calculation of heat transfer rate distribution (convection and radiation) with or without boundary layer coolant and/or thermal barrier coating layer
Film cooling analysis
Radiation cooling analysis
Regenerative cooling analysis:
  • coaxial shell jacket
  • tubular jacket
  • jacket with milled channels
Thermal analysis of thrust chambers with combined cooling (radiation + film + regenerative)
Estimation of hydraulic losses in the cooling passages
Estimation of friction thrust loss
Estimation of divergence thrust loss for nozzle with truncated ideal nozzle contour (TIC)
Calculation of thermal transport properties
Scripting module to solve user's own problems, extending standard capabilities of the program
Propellant analysis tool to evaluate different propellant compositions, with stepwise replacement of one component with another one
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
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
Producing publication-quality plots (in raster or vector format)
Output of results to PDF or ODF format
Analysis of monopropellant and bipropellant rocket engines
Analysis of rocket propulsion engines with an arbitrary set of propellant components (multipropellant systems)
Robust, proven and industry-accepted Gibbs free energy minimization approach is used to obtain the combustion composition
Calculation of performance for a finite- and infinite-area combustion chambers
Analysis of nozzle flows with shifting and frozen chemical equilibrium
Calculation of thrust coefficient, characteristic velocity and specific impulse (sea level, optimum expansion, vacuum)
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 (delivered) nozzle performance
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
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
Tool for import components from PROPEP or CEA2 species databases
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)
Multi-platform graphical user interface for Microsoft® Windows™ (both x86 and x86-64), as well as for Linux
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
Results output in SI or U.S. customary units
Output of results to Plain Text or HTML format
Graphical output of results of altitude and throttled engine performance analysis
Printing results of analysis
Two modes for comfortable work: Express Analysis and Extended Analysis

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