Design of a supersonic rocket nozzle using MOC
Abstract
The objective of this effort was to design and validate a supersonic nozzle given rocket engine combustion chamber properties. The nozzle contour was calculated using the method of characteristics. The MOC program originally written in MATLAB has been modified and translated to Python to make it user friendly. Also python scripts were developed to generate required input mesh and other parameters for CFD program. The flowfield of supersonic nozzle was solved using an opensource CFD toolbox OpenFOAM. The exit flow condition from CFD results has been analysed to met with the design conditions. Some recommendations and future pathways of this project are also discussed.
