{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/72992"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/72992","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05","abstract":"U of I Only Restriction Lifted for Item 73181 on 2017-01-22T10:15:29Z.","abstract_html":"U of I Only Restriction Lifted for Item 73181 on 2017-01-22T10:15:29Z.","abstract_has_math":false,"creators":["Hale, Jason"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Elliott, Gregory S.","Dutton, J.C."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-01-21T19:55:26Z","date_published":"2015-01-21T19:55:26Z","updated_at":"2026-07-22T22:26:07Z","subjects":["Taylor Maccoll","Cone Flow","Shock Boundary Layer Interaction (SBLI)","Shock Wave Boundary Layer Interaction","Pressure Sensitive Paint","Particle Image Velocimetry","Supersonic"],"languages":["en"],"rights":["Copyright 2014 Jason Hale"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/72992","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Elliott, Gregory S.","Dutton, J.C."]},{"key":"dc:creator","label":"Author","values":["Hale, Jason"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2015-01-21T19:55:26Z","2017-01-22T10:15:29Z","2014-12","2015-01-21"]},{"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":["Taylor Maccoll","Cone Flow","Shock Boundary Layer Interaction (SBLI)","Shock Wave Boundary Layer Interaction","Pressure Sensitive Paint","Particle Image Velocimetry","Supersonic"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2014 Jason Hale"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/72992"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["U of I Only Restriction Lifted for Item 73181 on 2017-01-22T10:15:29Z.","The interaction between an impinging conical shock wave with a plane compressible turbulent boundary layer has been studied at Mach 2.05. Surface oil flow and pressure-sensitive paint (PSP) data were obtained beneath the oncoming boundary layer, while schlieren and particle image velocimetry (PIV) data were obtained in the streamwise/wall-normal (x-y) plane. Oil flow data suggested that the interaction causes two-dimensional (2D) separation near the centerline, and outside of this region three-dimensional (3D) separation that propagates fluid away from the centerline toward the sidewall. PSP results showed relatively constant upstream-influence length across the inviscid shock trace. PSP also revealed significant spanwise and streamwise expansion just downstream of the shock trace, unlike the qualitatively similar two-dimensional, wedge-generated oblique shock/boundary-layer interaction. Schlieren data suggested that the flow through the interaction was unseparated, and that there is significant unsteadiness in interaction position away from the centerline due to variation in the incoming boundary layer. PIV data showed the convection of large-scale vortical structures at velocities on the order of the streamwise velocity at the vortex center. These structures were smoothed out in the interaction. The PIV data moreover confirmed the downstream expansion shown by the PSP as well as a mean lack of flow separation. However, PIV suggested that there were some cases of instantaneous separation. Overall, the interaction diverts fluid away from a low pressure zone a little way downstream of the shock. Ultimately, the geometric three-dimensionality of the problem manifests as a preferred three-dimensionality of fluid transport next to the wall, unlike the qualitatively similar, 2D oblique shock-wave/boundary-layer interaction.","Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2014-11-21T20:10:14Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 1 Hale_Jason.pdf: 6885418 bytes, checksum: e4361ea8f1e89030f77b3ed7b26597fb (MD5)","Made available in DSpace on 2015-01-21T19:55:26Z (GMT). No. of bitstreams: 2 Jason_Hale.pdf: 6889525 bytes, checksum: 2f9b9e67dbe7c4c2f0c0663c6bf5b554 (MD5) Whole_Doc_rev3c.docx: 17187648 bytes, checksum: e5fec6772c81ad71574202c4ddbecad1 (MD5)","Embargo set by: Seth Robbins for item 73181 Lift date: 2017-01-21T19:56:18Z Reason: Author requested U of Illinois access only (OA after 2yrs) in Vireo ETD system"]},{"key":"dc:title","label":"Title","values":["Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05"]}]}],"canonical_facts":{"dc:contributor":["Elliott, Gregory S.","Dutton, J.C."],"dc:creator":["Hale, Jason"],"dc:date":["2015-01-21T19:55:26Z","2017-01-22T10:15:29Z","2014-12","2015-01-21"],"dc:description":["U of I Only Restriction Lifted for Item 73181 on 2017-01-22T10:15:29Z.","The interaction between an impinging conical shock wave with a plane compressible turbulent boundary layer has been studied at Mach 2.05. Surface oil flow and pressure-sensitive paint (PSP) data were obtained beneath the oncoming boundary layer, while schlieren and particle image velocimetry (PIV) data were obtained in the streamwise/wall-normal (x-y) plane. Oil flow data suggested that the interaction causes two-dimensional (2D) separation near the centerline, and outside of this region three-dimensional (3D) separation that propagates fluid away from the centerline toward the sidewall. PSP results showed relatively constant upstream-influence length across the inviscid shock trace. PSP also revealed significant spanwise and streamwise expansion just downstream of the shock trace, unlike the qualitatively similar two-dimensional, wedge-generated oblique shock/boundary-layer interaction. Schlieren data suggested that the flow through the interaction was unseparated, and that there is significant unsteadiness in interaction position away from the centerline due to variation in the incoming boundary layer. PIV data showed the convection of large-scale vortical structures at velocities on the order of the streamwise velocity at the vortex center. These structures were smoothed out in the interaction. The PIV data moreover confirmed the downstream expansion shown by the PSP as well as a mean lack of flow separation. However, PIV suggested that there were some cases of instantaneous separation. Overall, the interaction diverts fluid away from a low pressure zone a little way downstream of the shock. Ultimately, the geometric three-dimensionality of the problem manifests as a preferred three-dimensionality of fluid transport next to the wall, unlike the qualitatively similar, 2D oblique shock-wave/boundary-layer interaction.","Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2014-11-21T20:10:14Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 1 Hale_Jason.pdf: 6885418 bytes, checksum: e4361ea8f1e89030f77b3ed7b26597fb (MD5)","Made available in DSpace on 2015-01-21T19:55:26Z (GMT). No. of bitstreams: 2 Jason_Hale.pdf: 6889525 bytes, checksum: 2f9b9e67dbe7c4c2f0c0663c6bf5b554 (MD5) Whole_Doc_rev3c.docx: 17187648 bytes, checksum: e5fec6772c81ad71574202c4ddbecad1 (MD5)","Embargo set by: Seth Robbins for item 73181 Lift date: 2017-01-21T19:56:18Z Reason: Author requested U of Illinois access only (OA after 2yrs) in Vireo ETD system"],"dc:identifier":["http://hdl.handle.net/2142/72992"],"dc:language":["en"],"dc:rights":["Copyright 2014 Jason Hale"],"dc:subject":["Taylor Maccoll","Cone Flow","Shock Boundary Layer Interaction (SBLI)","Shock Wave Boundary Layer Interaction","Pressure Sensitive Paint","Particle Image Velocimetry","Supersonic"],"dc:title":["Interaction between a conical shock wave and a plane compressible turbulent boundary layer at Mach 2.05"],"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":"2026-07-22T22:26:07Z"}