سال انتشار: ۱۳۸۸

محل انتشار: هشتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۵

نویسنده(ها):

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

چکیده:

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.