{"id":{"repo_id":"utc","oai_identifier":"oai:scholar.utc.edu:theses-1899"},"canonical_url":"https://search.dev.ndltd.org/etd/utc/oai:scholar.utc.edu:theses-1899","repository":{"repo_id":"utc","name":"University of Tennessee - Chattanooga","base_url":"https://scholar.utc.edu/do/oai/"},"display":{"title":"Creation of a Trimmed Powered Aerodynamic Database for a Generic Hypersonic Vehicle","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.","abstract_html":"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.","abstract_has_math":false,"creators":["DeBardelaben, Cannon"],"institution":"University of Tennessee at Chattanooga","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":null,"school":null,"contributors":["Sreenivas, Kidambi","Margraves, Charles; Newman, James C., III","College of Engineering and Computer Science"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":null,"date_issued":"","date_published":null,"updated_at":"2026-07-24T05:47:06Z","subjects":["Aerospace engineering","Computational fluid dynamics","Hypersonic planes"],"languages":["English","eng"],"rights":[],"rights_urls":["http://rightsstatements.org/vocab/InC/1.0/"],"identifier_entries":[]},"links":{"outbound_url":"https://scholar.utc.edu/theses/732","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Sreenivas, Kidambi","Margraves, Charles; Newman, James C., III","College of Engineering and Computer Science"]},{"key":"dc:creator","label":"Author","values":["DeBardelaben, Cannon"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2021-12-01T08:00:00Z"]},{"key":"dc:publisher","label":"Institution","values":["University of Tennessee at Chattanooga","Chattanooga (Tenn.)"]},{"key":"dc:relation","label":"Dc Relation","values":["Masters Theses and Doctoral Dissertations"]},{"key":"dc:type","label":"Dc Type","values":["Masters theses","Text"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Aerospace engineering","Computational fluid dynamics","Hypersonic planes"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["English","eng"]},{"key":"dc:rights","label":"Dc Rights","values":["http://rightsstatements.org/vocab/InC/1.0/"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://scholar.utc.edu/theses/732"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Dept. of Mechanical Engineering","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."]},{"key":"dc:description.abstract","label":"Abstract","values":["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."]},{"key":"dc:title","label":"Title","values":["Creation of a Trimmed Powered Aerodynamic Database for a Generic Hypersonic Vehicle"]}]}],"canonical_facts":{"dc:contributor":["Sreenivas, Kidambi","Margraves, Charles; Newman, James C., III","College of Engineering and Computer Science"],"dc:creator":["DeBardelaben, Cannon"],"dc:date":["2021-12-01T08:00:00Z"],"dc:description":["Dept. of Mechanical Engineering","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."],"dc:description.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."],"dc:identifier":["https://scholar.utc.edu/theses/732"],"dc:language":["English","eng"],"dc:publisher":["University of Tennessee at Chattanooga","Chattanooga (Tenn.)"],"dc:relation":["Masters Theses and Doctoral Dissertations"],"dc:rights":["http://rightsstatements.org/vocab/InC/1.0/"],"dc:subject":["Aerospace engineering","Computational fluid dynamics","Hypersonic planes"],"dc:title":["Creation of a Trimmed Powered Aerodynamic Database for a Generic Hypersonic Vehicle"],"dc:type":["Masters theses","Text"]},"updated_at":"2026-07-24T05:47:06Z"}