Projects / Rocket Propulsion Analysis

Rocket Propulsion Analysis

Rocket Propulsion Analysis (RPA) is a tool for the performance prediction of rocket engines. By providing a few engine parameters such as combustion chamber pressure, used propellant components, and nozzle parameters, the program obtains chemical equilibrium composition of combustion products, determines its thermodynamic properties, and predicts the theoretical rocket performance. A robust, proven, and industry-accepted Gibbs free energy minimization approach is used to obtain the combustion composition. It can perform analysis of nozzle flows with shifting and frozen chemical equilibrium, optimization 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, and nested analysis: stepping of up to four independent variables (component ratio, chamber pressure, nozzle inlet conditions, and nozzle exit conditions).

Operating Systems

Recent releases

  •  18 Oct 2011 09:11

    Release Notes: Calculation of additional nozzle stations was added. Calculated thrust was added to the altitude performance table, and calculated thrust (at SL, opt, and vac conditions) was added to the throttled performance table. In both Nested Analysis and Propellant Analysis tools, any of calculated parameters (Is, Tc, c*, Cf) can be plotted on the "parameter vs. O/F ratio" diagram. Calculation of estimated delivered performance was improved.

    •  16 Apr 2011 07:20

      Release Notes: This release added the ability to define combustion chamber length by either L* or L'. Calculation of estimated delivered altitude performance was added along with calculation of estimated delivered performance of a throttled engine. The initial parabola angle for parabolic nozzles can now be defined. A mistake in the chamber sizing module that allowed definition of L* in SI units only, ignoring other selected units (in, ft, mm) was fixed along with an error in parabolic nozzle calculation for nozzles with low area ratio Ae/At.

      •  14 Mar 2011 22:56

        Release Notes: Calculation of thermal transport properties. Improved performance estimation for solid propellants. A fix for a mistake that caused a program crash when loading a configuration file with a defined diameter of the nozzle throat. A fix for a mistake in the calculation of sonic velocity at the nozzle throat section for reaction products with a condensed phase.

        •  24 Feb 2011 09:51

          Release Notes: This version is available in two editions: the freeware Lite Edition and the commercial Standard Edition. The new features in the Standard Edition are a scripting module to solve the user's own problems; a propellant analysis tool to evaluate different propellant compositions, with stepwise replacement of one component with another one; the ability to determine combustion chamber size for a given thrust, propellant mass flow rate, or throat diameter; the ability to design parabolic or MOC TIC nozzle contours and export the resulting contour to DXF file; and the ability to produce publication-quality plots (in raster or vector format).


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