Committee Chair

Sreenivas, Kidambi

Committee Member

Margraves, Charles; Newman, James C., III

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 purpose of this thesis is to propose and evaluate a methodology for creating an inviscid trimmed powered database for a generic airbreathing hypersonic vehicle. The database was created using the cartesian flow solver Cart3D. Propulsion effects were coupled to the airframe and inlet by using conditions at the inlet of the combustor to determine conditions at the exit of the combustor. This was done by solving the quasi-one-dimensional momentum equation with heat addition. Selected trajectory points were also evaluated using the viscous solver, FUN3D. The viscous solutions contain effects such as boundary layer separation which had a pronounced effect on the computed axial force. In all cases, the viscous solutions predicted a lower thrust than the inviscid solutions, mainly due to the presence of viscous shear stresses. Experimental data would be required to further evaluate the validity of the assumptions made in both the inviscid and viscous analysis.

Acknowledgments

I would like to thank Dr. Kidambi Sreenivas for answering my endless questions and serving as my advisor and committee chair. In addition, I would like to thank Drs. Newman and Margraves for furthering my understanding of the material contained in this thesis, as well as serving on my committee. I would also like to thank my research partners Jason DeHay, Jameson Snuggs, and Alex Snyder. Funding was provided through the Reusable Hypersonic Vehicle Structures program by Air Force Research Laboratory, Aerospace System Directorate, High Speed Systems Division (AFRL/RQH), Prime Contract Number FA8650-18-C-2253. Computing resources were provided by the SimCenter at the University of Tennessee at Chattanooga. In particular, the "EPYC" and "ETEST" clusters, acquired via NSF Award #1925603, were used for the viscous simulations. The "Firefly" cluster was used for the inviscid simulations. Images were created by using FieldView as provided by FieldView CFD, Inc. through its University Partners 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

12-2021

Subject

Aerospace engineering; Computational fluid dynamics; Hypersonic planes

Keyword

Aerospace; Computational Fluid Dynamics; High-speed

Document Type

Masters theses

DCMI Type

Text

Extent

xv, 105 leaves

Language

English

Rights

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

License

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

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