Numerical simulation of supersonic combustion in convergent-divergent duct for hypersonic propulsion
by
Tohid Alizadeh
iran-esfahan-malekashtar university of thechnology-department of aerospace engineering
Coauthors: Prof. Mirzabozorg

Recently, renewed interest on the scramjet engine has been demonstrated through the many international activities along countries.Here computations on scramjet combustor are described of the combusting flows within a hydrogen fueled model supersonic combustion ramjet (scramjet). In this research first we generate the shock waves in a special duct with turbulence models then injected the fueled hydrogen into the scramjet combustor from the intake wall. In all results for hypersonic flows the mach number was 6.5. simulation result show good generation of shock waves in duct then accomplishment of supersonic combustion in combustion chamber.

Date received: May 20, 2008

Copyright © 2008 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # caxe-24.