RSS 1 project tagged "Simulation"

Download Website Updated 18 Oct 2011 Rocket Propulsion Analysis

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Pop 59.71
Vit 2.51

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).

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