Design of Supersonic Nozzle Using CFD

Abstract

The goal of this research is to design a minimum length supersonic nozzle (MLN) and develops a computer code which uses the Method of Characteristics to design supersonic nozzle contours for isentropic, inviscid, irrotational supersonic flows of any working fluid for any user-defined exit Mach number. The contours were compared to theoretical isentropic exit area ratios and exit area ratios for GA10 nozzle, the percentage of error does not exceed 2% for all exit area ratios, and percentage of error does not exceed 5% for all mass flow rates. Also the contour was compared to Britton’s code, where the difference does not exceed 10% of Britton’s code results.