Committee Chair

Sreenivas, Kidambi

Committee Member

Newman III, James; Margraves, Charles

Department

Dept. of Mechanical Engineering

College

College of Engineering and Computer Science

Publisher

University of Tennessee at Chattanooga

Place of Publication

Chattanooga (Tenn.)

Abstract

The BAM6QT is a hypersonic wind tunnel that was simulated with a 7-degree half-angle cone with diameters ranging from 4 to 7-inches, three different cone setups, and viscous and inviscid flow computations. These tests were then compared to determine what effects would cause the tunnel to unstart. Unstarting refers to flow not reaching Mach 6 at the apex of the cone or reflection shocks impinging on the surface of the cone causing undesired flow characteristics. There were three main conclusions that were made from this study, initially, it was found that when the BAM6QT was simulated with viscous flow and a 5.5-inch diameter cone with sting and or sting and support the tunnel would unstart. Secondary findings determined that viscous flow and sting and or sting and sting support are essential to the results. The tunnel unstarts due to shock and boundary layer interaction on the 5.5-inch diameter cone.

Acknowledgments

I would like to thank Dr. Kidambi Sreenivas my advisor and committee chair for always being there for guidance and clear thoughts. A special thank you to Dr. Margraves and Dr. Ranjan for teaching me courses in fluids and thermodynamics that have prepared me to understand my thesis topic clearly. Special thank you to Jason Dehay, Cannon Debardelaben, James Snuggs, and Nina Rice my coworkers and research partners for listening when I needed to talk about a problem aloud. Thank you to Purdue University and the BAM6QT team for providing available data and for answering countless questions. Computing resources were provided by the University of Tennessee Chattanooga's SimCenter. Images were created using FieldView, as provided by FieldView CFD, inc. through its University Partner Program.

Degree

M. S.; A thesis submitted to the faculty of the University of Tennessee at Chattanooga in partial fulfillment of the requirements of the degree of Master of Science.

Date

8-2022

Subject

Aerodynamics, Hypersonic; Hypersonic wind tunnels

Keyword

Hypersonic; Wind Tunnel; 7-Degree Half Angle Cone; Aerospace; Mechanical

Document Type

Masters theses

DCMI Type

Text

Extent

xvi, 91 leaves

Language

English

Rights

http://rightsstatements.org/vocab/InC/1.0/

License

http://creativecommons.org/licenses/by/4.0/

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