{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/85067"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/85067","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Effects of Supercooled Large -Droplet Icing on Airfoil Aerodynamics","abstract":"The effects of simulated ice shape on the NLF 0414 were quite different from the NACA 23012m. There was little variation of lift when the simulated ice-shape location was varied from 2% to 20% chord. The large losses in lift occurred when the ice shape was located downstream of 30% chord, and the separation bubble formed over the adverse pressure gradient of the clean airfoil, which started at 75% chord. The effect of the ice shape on the NLF 0414 was not as severe as on the NACA 23012m because the lift was much more aft loaded.","abstract_html":"The effects of simulated ice shape on the NLF 0414 were quite different from the NACA 23012m. There was little variation of lift when the simulated ice-shape location was varied from 2% to 20% chord. The large losses in lift occurred when the ice shape was located downstream of 30% chord, and the separation bubble formed over the adverse pressure gradient of the clean airfoil, which started at 75% chord. The effect of the ice shape on the NLF 0414 was not as severe as on the NACA 23012m because the lift was much more aft loaded.","abstract_has_math":false,"creators":["Lee, Sam"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"Ph.D.","degree_level":"Dissertation","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Bragg, Michael B."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-09-25T22:34:17Z","date_published":"2015-09-25T22:34:17Z","updated_at":"2026-07-22T22:26:24Z","subjects":["Engineering, Aerospace"],"languages":["eng"],"rights":[],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["(MiAaPQ)AAI3017141"],"render_values":[{"text":"(MiAaPQ)AAI3017141","href":null,"code":true}]}]},"links":{"outbound_url":"http://hdl.handle.net/2142/85067","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Bragg, Michael B."]},{"key":"dc:creator","label":"Author","values":["Lee, Sam"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2015-09-25T22:34:17Z","10000-01-01","2001"]},{"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":["Dissertation"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Ph.D."]},{"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":["Engineering, Aerospace"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["eng"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/85067","(MiAaPQ)AAI3017141"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["The effects of simulated ice shape on the NLF 0414 were quite different from the NACA 23012m. There was little variation of lift when the simulated ice-shape location was varied from 2% to 20% chord. The large losses in lift occurred when the ice shape was located downstream of 30% chord, and the separation bubble formed over the adverse pressure gradient of the clean airfoil, which started at 75% chord. The effect of the ice shape on the NLF 0414 was not as severe as on the NACA 23012m because the lift was much more aft loaded.","Made available in DSpace on 2015-09-25T22:34:17Z (GMT). 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There was little variation of lift when the simulated ice-shape location was varied from 2% to 20% chord. The large losses in lift occurred when the ice shape was located downstream of 30% chord, and the separation bubble formed over the adverse pressure gradient of the clean airfoil, which started at 75% chord. The effect of the ice shape on the NLF 0414 was not as severe as on the NACA 23012m because the lift was much more aft loaded.","Made available in DSpace on 2015-09-25T22:34:17Z (GMT). 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