Tohid alizadeh - Master of sience in Aerospace Engineering, Iran-Esfahan-Malek Ashtar university of technology
mohsen Aghaseyyed mirzabozorg - Associate Professor, Iran-Esfahan-Malek Ashtar university of technology
mahmood adami - Associate Professor, Iran-Esfahan-Malek Ashtar university of technology
shapour jafargolinejad - Master of sience in Electronic engineering, Iran-Esfahan-Malek Ashtar university of technology

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 1ueled hydrogen into the scramjet combustor from the intake wall. The turbulence model that is used in this research is {k- ).SST. 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.

Scramjet, Shock Waves, Duct, Hypersonic flows, Supersonic combustion