![]() The program takes the available selections and specifications made by the user and outputs key design parameters calculated from the input variables. Chamber dimensions, propellant selections, and injector selection between doublet or triplet allow for further refinement of the desired rocket system design. ![]() The program also allows for the selection of common nozzle profiles including 80% rao, conical, a user selected percentage bell, and a minimum length nozzle (MLN) using method of characteristics (MOC). The program aids in unifying the nozzle, chamber and injector portions of a rocket propulsion system design effort quickly and efficiently using a streamlined graphical user interface (GUI). This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort.
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