{"id":{"repo_id":"utc","oai_identifier":"oai:scholar.utc.edu:theses-1990"},"canonical_url":"https://search.dev.ndltd.org/etd/utc/oai:scholar.utc.edu:theses-1990","repository":{"repo_id":"utc","name":"University of Tennessee - Chattanooga","base_url":"https://scholar.utc.edu/do/oai/"},"display":{"title":"A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures","abstract":"A CFD methodology for simulating various configurations of three selected wings in Purdue University’s Boeing Air Force Office of Scientific Research Mach 6 Quiet Tunnel (BAM6QT) is presented. The NASA-developed computational fluid dynamics (CFD) code, FUN3D, is used to calculate forces, moments, and temperature gradients. Wings with an attached elevon are also simulated, and the large wing with elevon case is used to study a moving elevon as well as static elevon deflections. A threshold frequency is found for the moving elevon where the moment imparted by the elevon increases with frequency. An attempt is made to detect unsteadiness around the 12 degree deflected elevon but it is likely more computational resources are needed for this study. Previous work from Alexander Snyder is built upon by attempting to model only the test section of the BAM6QT by using a boundary layer profile inlet condition, but results are not confirmed.","abstract_html":"A CFD methodology for simulating various configurations of three selected wings in Purdue University’s Boeing Air Force Office of Scientific Research Mach 6 Quiet Tunnel (BAM6QT) is presented. The NASA-developed computational fluid dynamics (CFD) code, FUN3D, is used to calculate forces, moments, and temperature gradients. Wings with an attached elevon are also simulated, and the large wing with elevon case is used to study a moving elevon as well as static elevon deflections. A threshold frequency is found for the moving elevon where the moment imparted by the elevon increases with frequency. An attempt is made to detect unsteadiness around the 12 degree deflected elevon but it is likely more computational resources are needed for this study. Previous work from Alexander Snyder is built upon by attempting to model only the test section of the BAM6QT by using a boundary layer profile inlet condition, but results are not confirmed.","abstract_has_math":false,"creators":["Snuggs, James"],"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":"2026-07-24T05:47:13Z","subjects":["Aerodynamics, Hypersonic","Hypersonic wind tunnels","Computational fluid dynamics"],"languages":["English","eng"],"rights":[],"rights_urls":["http://rightsstatements.org/vocab/InC/1.0/"],"identifier_entries":[]},"links":{"outbound_url":"https://scholar.utc.edu/theses/819","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":["Snuggs, James"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2023-08-01T07:00:00Z"]},{"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":["Aerodynamics, Hypersonic","Hypersonic wind tunnels","Computational fluid dynamics"]}]},{"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/819"]}]},{"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":["A CFD methodology for simulating various configurations of three selected wings in Purdue University’s Boeing Air Force Office of Scientific Research Mach 6 Quiet Tunnel (BAM6QT) is presented. The NASA-developed computational fluid dynamics (CFD) code, FUN3D, is used to calculate forces, moments, and temperature gradients. Wings with an attached elevon are also simulated, and the large wing with elevon case is used to study a moving elevon as well as static elevon deflections. A threshold frequency is found for the moving elevon where the moment imparted by the elevon increases with frequency. An attempt is made to detect unsteadiness around the 12 degree deflected elevon but it is likely more computational resources are needed for this study. Previous work from Alexander Snyder is built upon by attempting to model only the test section of the BAM6QT by using a boundary layer profile inlet condition, but results are not confirmed."]},{"key":"dc:title","label":"Title","values":["A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures"]}]}],"canonical_facts":{"dc:contributor":["Sreenivas, Kidambi","Margraves, Charles; Newman, James C., III","College of Engineering and Computer Science"],"dc:creator":["Snuggs, James"],"dc:date":["2023-08-01T07:00:00Z"],"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":["A CFD methodology for simulating various configurations of three selected wings in Purdue University’s Boeing Air Force Office of Scientific Research Mach 6 Quiet Tunnel (BAM6QT) is presented. The NASA-developed computational fluid dynamics (CFD) code, FUN3D, is used to calculate forces, moments, and temperature gradients. Wings with an attached elevon are also simulated, and the large wing with elevon case is used to study a moving elevon as well as static elevon deflections. A threshold frequency is found for the moving elevon where the moment imparted by the elevon increases with frequency. An attempt is made to detect unsteadiness around the 12 degree deflected elevon but it is likely more computational resources are needed for this study. Previous work from Alexander Snyder is built upon by attempting to model only the test section of the BAM6QT by using a boundary layer profile inlet condition, but results are not confirmed."],"dc:identifier":["https://scholar.utc.edu/theses/819"],"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":["Aerodynamics, Hypersonic","Hypersonic wind tunnels","Computational fluid dynamics"],"dc:title":["A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures"],"dc:type":["Masters theses","Text"]},"updated_at":"2026-07-24T05:47:13Z"}