Design of a supersonic rocket nozzle using MOC

Contour generated from MOC for divergent section of C-D rocket nozzle.

Associated with: VGEC, Ahmedabad
Started: July, 2020 | Completed: August, 2020
Tools: python, OpenFOAM, ANSYS

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 analyzed to met with the design conditions. Some recommendations and future pathways of this project are also discussed.

Gallery

CFD Results of various properties distributed inside nozzle

Mach No distribution inside nozzle. Comparison of CFD and Analytical Results.

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