Keywords

supersonic crossflow, Schlieren visualization

Abstract

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.

Notes

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Graduation Date

2007

Semester

Spring

Advisor

Petersen, Eric

Degree

Master of Science in Aerospace Engineering (M.S.A.E.)

College

College of Engineering and Computer Science

Department

Mechanical, Materials, and Aerospace Engineering

Degree Program

Aerospace Engineering

Format

application/pdf

Identifier

CFE0001637

URL

http://purl.fcla.edu/fcla/etd/CFE0001637

Language

English

Release Date

May 2007

Length of Campus-only Access

None

Access Status

Masters Thesis (Open Access)

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