Numerical Simulation of Supersonic Combustion in convergent-divergent duct for Hypersonic Propulsion
Publish place: The 8th Conference of Iranian Aerospace Society
Publish Year: 1388
نوع سند: مقاله کنفرانسی
زبان: English
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شناسه ملی سند علمی:
AEROSPACE08_177
تاریخ نمایه سازی: 5 شهریور 1388
Abstract:
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.
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Authors
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