Numerical Simulation of Supersonic Combustion in convergent-divergent duct for Hypersonic Propulsion

سال انتشار: 1388
نوع سند: مقاله کنفرانسی
زبان: انگلیسی
مشاهده: 1,785

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شناسه ملی سند علمی:

AEROSPACE08_177

تاریخ نمایه سازی: 5 شهریور 1388

چکیده مقاله:

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.

نویسندگان

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