Abstract
This paper describes an effort to develop an efficient CFD tool to analyze the flow through the Scramjet with cavity recessed combustion chamber. Cavities has become one of the main interest area of the hypersonic propulsion community due to its effect on flame-holding and mixing efficiency. Cavities stabilize the flow and so enhance the supersonic combustion. Coupled Euler and finite rate chemical reaction equations are employed. Hydrocarbons are one of the most efficient fuels to be used in Scramjets. Reduced chemical reactions of Ethylene-Air is used in this study. Two different fuel injection configurations are compared; fuel injection only upstream of the cavity and fuel injection both from the upstream and downstream of the cavity. Fuel injection from only upstream of the cavity showed a better combustion performance since the amount of unburned fuel is less at the combustor exit.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
