{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/104947"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/104947","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Direct simulation of the fluid-structure interaction of a compliant panel in a hypersonic compression ramp flow","abstract":"Made available in DSpace on 2019-08-23T20:05:24Z (GMT). No. of bitstreams: 2 SULLIVAN-THESIS-2019.pdf: 17201247 bytes, checksum: d0a3b3cb0abcb1c32abeaa87d376612e (MD5) LICENSE.txt: 4212 bytes, checksum: 6e46c83f39344ca0c821874c7c9c44e6 (MD5) Previous issue date: 2019-04-26","abstract_html":"Made available in DSpace on 2019-08-23T20:05:24Z (GMT). No. of bitstreams: 2 SULLIVAN-THESIS-2019.pdf: 17201247 bytes, checksum: d0a3b3cb0abcb1c32abeaa87d376612e (MD5) LICENSE.txt: 4212 bytes, checksum: 6e46c83f39344ca0c821874c7c9c44e6 (MD5) Previous issue date: 2019-04-26","abstract_has_math":false,"creators":["Sullivan, Bryson"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Bodony, Daniel J."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2019,"date_issued":"2019-08-23T20:05:24Z","date_published":"2019-08-23T20:05:24Z","updated_at":"2026-07-22T22:24:42Z","subjects":["hypersonic, compression ramp, fluid-structure interaction, aerothermoelastic, aeroelasticity, piston theory"],"languages":["en"],"rights":["Copyright 2019 Bryson Sullivan"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/104947","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Bodony, Daniel J."]},{"key":"dc:creator","label":"Author","values":["Sullivan, Bryson"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2019-08-23T20:05:24Z","2019-04-26","2019-05"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["M.S."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["hypersonic, compression ramp, fluid-structure interaction, aerothermoelastic, aeroelasticity, piston theory"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2019 Bryson Sullivan"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/104947"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["Made available in DSpace on 2019-08-23T20:05:24Z (GMT). No. of bitstreams: 2 SULLIVAN-THESIS-2019.pdf: 17201247 bytes, checksum: d0a3b3cb0abcb1c32abeaa87d376612e (MD5) LICENSE.txt: 4212 bytes, checksum: 6e46c83f39344ca0c821874c7c9c44e6 (MD5) Previous issue date: 2019-04-26","Sustained flight at hypersonic speeds presents a challenge to robust vehicle design and control. An extreme aerothermal environment acting on geometrically-thin, multifunctional structures can result in significant static and dynamic structural deformations of the vehicle and its subcomponents. In particular, for a control surface-motivated scenario, the adverse pressure gradient generated by a compression ramp can produce a large region of subsonic, separated flow with the potential to degrade accurate estimation of surface loading by traditional hypersonic aerodynamic methods such as piston theory. The present work details high-fidelity, coupled fluid-thermal-structure interaction (FTSI) simulations of laminar, unsteady 2D flow at Mach 6.04 over a 35-degree compression ramp with an embedded compliant panel. Surface-pressure loading generated by the corner shock wave boundary layer Interaction (SWBLI) is compared between compliant and non-compliant compression ramp configurations, and SWBLI-excited response of the compliant panel is demonstrated. An analytical model based on Rayleigh's method is introduced which, given the maximum amplitude of vibration, predicts the nonlinear frequency of a compliant panel to within an average error of 8.3% over several orders of magnitude in flexural rigidity. Maximum observed heat transfer rates to the panel were diminished for the compliant panel cases relative to the rigid case, believed to be caused by a break-up in structure of the oscillating shear layer due to the motion of the panel. Reduced-order models, such as shock expansion/ local piston theory (SE/LPT), are computed for each panel and were found to perform well with a modification to account the influence of the corner separation region. Reynolds analogy for estimating heat flux was found to work reasonably well for the rigid case, but lost accuracy when applied to the thinnest panels and largest deflections.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2019-08-22 without embargo terms","The student, Bryson Sullivan, accepted the attached license on 2019-04-26 at 10:30.","The student, Bryson Sullivan, submitted this Thesis for approval on 2019-04-26 at 10:37.","This Thesis was approved for publication on 2019-04-26 at 13:03.","DSpace SAF Submission Ingestion Package generated from Vireo submission #13942 on 2019-08-22 at 14:47:04"]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Direct simulation of the fluid-structure interaction of a compliant panel in a hypersonic compression ramp flow"]}]}],"canonical_facts":{"dc:contributor":["Bodony, Daniel J."],"dc:creator":["Sullivan, Bryson"],"dc:date":["2019-08-23T20:05:24Z","2019-04-26","2019-05"],"dc:description":["Made available in DSpace on 2019-08-23T20:05:24Z (GMT). No. of bitstreams: 2 SULLIVAN-THESIS-2019.pdf: 17201247 bytes, checksum: d0a3b3cb0abcb1c32abeaa87d376612e (MD5) LICENSE.txt: 4212 bytes, checksum: 6e46c83f39344ca0c821874c7c9c44e6 (MD5) Previous issue date: 2019-04-26","Sustained flight at hypersonic speeds presents a challenge to robust vehicle design and control. An extreme aerothermal environment acting on geometrically-thin, multifunctional structures can result in significant static and dynamic structural deformations of the vehicle and its subcomponents. In particular, for a control surface-motivated scenario, the adverse pressure gradient generated by a compression ramp can produce a large region of subsonic, separated flow with the potential to degrade accurate estimation of surface loading by traditional hypersonic aerodynamic methods such as piston theory. The present work details high-fidelity, coupled fluid-thermal-structure interaction (FTSI) simulations of laminar, unsteady 2D flow at Mach 6.04 over a 35-degree compression ramp with an embedded compliant panel. Surface-pressure loading generated by the corner shock wave boundary layer Interaction (SWBLI) is compared between compliant and non-compliant compression ramp configurations, and SWBLI-excited response of the compliant panel is demonstrated. An analytical model based on Rayleigh's method is introduced which, given the maximum amplitude of vibration, predicts the nonlinear frequency of a compliant panel to within an average error of 8.3% over several orders of magnitude in flexural rigidity. Maximum observed heat transfer rates to the panel were diminished for the compliant panel cases relative to the rigid case, believed to be caused by a break-up in structure of the oscillating shear layer due to the motion of the panel. Reduced-order models, such as shock expansion/ local piston theory (SE/LPT), are computed for each panel and were found to perform well with a modification to account the influence of the corner separation region. Reynolds analogy for estimating heat flux was found to work reasonably well for the rigid case, but lost accuracy when applied to the thinnest panels and largest deflections.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2019-08-22 without embargo terms","The student, Bryson Sullivan, accepted the attached license on 2019-04-26 at 10:30.","The student, Bryson Sullivan, submitted this Thesis for approval on 2019-04-26 at 10:37.","This Thesis was approved for publication on 2019-04-26 at 13:03.","DSpace SAF Submission Ingestion Package generated from Vireo submission #13942 on 2019-08-22 at 14:47:04"],"dc:format":["application/pdf"],"dc:identifier":["http://hdl.handle.net/2142/104947"],"dc:language":["en"],"dc:rights":["Copyright 2019 Bryson Sullivan"],"dc:subject":["hypersonic, compression ramp, fluid-structure interaction, aerothermoelastic, aeroelasticity, piston theory"],"dc:title":["Direct simulation of the fluid-structure interaction of a compliant panel in a hypersonic compression ramp flow"],"dc:type":["text"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis"],"thesis:degree_name":["M.S."],"thesis:institution_name":["University of Illinois at Urbana-Champaign"]},"updated_at":"2026-07-22T22:24:42Z"}