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SUPERSONIC CROSSFLOW VISUALIZATION USING THE UNIVERSITY OF CENTRAL FLORIDA SUPERSONIC WIND TUNNEL

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Date Issued:
2007
Abstract/Description:
The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas is injected into a supersonic free stream, a dedicated test section was developed which was attached to the existing supersonic wind tunnel at the University of Central Florida. A Schlieren system was developed to visualize the associated flow fields and to provide a tool for future high-speed aerodynamic research. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In addition to a description and analysis of the resultant data, this thesis also serves as a reference for future research and work done with the UCF supersonic wind tunnel and the Schlieren system. The results agree with the literature, and the Schlieren images obtained show the associated shock and flow structures that are expected with a jet in cross flow.
Title: SUPERSONIC CROSSFLOW VISUALIZATION USING THE UNIVERSITY OF CENTRAL FLORIDA SUPERSONIC WIND TUNNEL.
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Name(s): Himmerich, Peter, Author
Petersen, Eric, Committee Chair
University of Central Florida, Degree Grantor
Type of Resource: text
Date Issued: 2007
Publisher: University of Central Florida
Language(s): English
Abstract/Description: The next generation air breathing engine that would enable an alternative to conventional air travel or suborbital flight is the supersonic ramjet engine (SCRAM) which requires a highly accelerated rate of fuel mixing and combustion. For this type of engine, one of the improvement opportunities lies in the injection of the fuel into the supersonic flow inside the combustor. In order to determine the flow field that develops when a sonic jet of secondary gas is injected into a supersonic free stream, a dedicated test section was developed which was attached to the existing supersonic wind tunnel at the University of Central Florida. A Schlieren system was developed to visualize the associated flow fields and to provide a tool for future high-speed aerodynamic research. Mixing of a cross flow jet with a supersonic free stream is a topic of interest in the field of hypersonic air travel. In addition to a description and analysis of the resultant data, this thesis also serves as a reference for future research and work done with the UCF supersonic wind tunnel and the Schlieren system. The results agree with the literature, and the Schlieren images obtained show the associated shock and flow structures that are expected with a jet in cross flow.
Identifier: CFE0001637 (IID), ucf:47230 (fedora)
Note(s): 2007-05-01
M.S.A.E.
Engineering and Computer Science, Department of Mechanical Materials and Aerospace Engineering
Masters
This record was generated from author submitted information.
Subject(s): supersonic crossflow
Schlieren visualization
Persistent Link to This Record: http://purl.flvc.org/ucf/fd/CFE0001637
Restrictions on Access: public
Host Institution: UCF

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