{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/89040"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/89040","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Measurement of unsteady aerodynamic characteristics of a subscale aerobatic aircraft in high angle-of-attack maneuvers","abstract":"High angle-of-attack flight testing was performed using the UIUC Subscale Sukhoi, which is a 35% scale, 2.6 m (102 in) wingspan Sukhoi 29S electric model aircraft that was developed at the University of Illinois at Urbana-Champaign. The aircraft was instrumented with a custom sensor data acquisition system that allowed the motion and control inputs of the aircraft to be captured at a rate of 100 Hz. During the spring, summer, and fall of 2015, the UIUC Subscale Sukhoi was flown through a variety of high angle of attack maneuvers, specifically unpowered aggravated stalls, descending harriers, walls, and wing rock flight, during which flight data was recorded by the sensor data acquisition system. The flight data recorded during the maneuvers was processed to produce flight path trajectory plots, time histories and aircraft aerodynamic coefficient data. These plots showed unsteady aerodynamic effects exhibited by the aircraft. Among these results was one version of wing rock, where given a certain aircraft configuration with constant control surface inputs, the aircraft would wing rock with a constant frequency while the lift and drag coefficient oscillated with rapidly increasing then decreasing amplitudes, which has yet to be described in the literature.","abstract_html":"High angle-of-attack flight testing was performed using the UIUC Subscale Sukhoi, which is a 35% scale, 2.6 m (102 in) wingspan Sukhoi 29S electric model aircraft that was developed at the University of Illinois at Urbana-Champaign. The aircraft was instrumented with a custom sensor data acquisition system that allowed the motion and control inputs of the aircraft to be captured at a rate of 100 Hz. During the spring, summer, and fall of 2015, the UIUC Subscale Sukhoi was flown through a variety of high angle of attack maneuvers, specifically unpowered aggravated stalls, descending harriers, walls, and wing rock flight, during which flight data was recorded by the sensor data acquisition system. The flight data recorded during the maneuvers was processed to produce flight path trajectory plots, time histories and aircraft aerodynamic coefficient data. These plots showed unsteady aerodynamic effects exhibited by the aircraft. Among these results was one version of wing rock, where given a certain aircraft configuration with constant control surface inputs, the aircraft would wing rock with a constant frequency while the lift and drag coefficient oscillated with rapidly increasing then decreasing amplitudes, which has yet to be described in the literature.","abstract_has_math":false,"creators":["Dantsker, Or Daniel"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Selig, Michael S."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2016,"date_issued":"2016-03-02T19:34:12Z","date_published":"2016-03-02T19:34:12Z","updated_at":"2026-07-22T22:26:32Z","subjects":["Aerodynamics","Unmanned Aerial Vehicle (uav)","Aerobatic","high angle-of-attack"],"languages":["en"],"rights":["Copyright 2015 Or D. Dantsker"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/89040","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Selig, Michael S."]},{"key":"dc:creator","label":"Author","values":["Dantsker, Or Daniel"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2016-03-02T19:34:12Z","2015-12-11","2015-12"]},{"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":["Aerodynamics","Unmanned Aerial Vehicle (uav)","Aerobatic","high angle-of-attack"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2015 Or D. Dantsker"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/89040"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["High angle-of-attack flight testing was performed using the UIUC Subscale Sukhoi, which is a 35% scale, 2.6 m (102 in) wingspan Sukhoi 29S electric model aircraft that was developed at the University of Illinois at Urbana-Champaign. The aircraft was instrumented with a custom sensor data acquisition system that allowed the motion and control inputs of the aircraft to be captured at a rate of 100 Hz. During the spring, summer, and fall of 2015, the UIUC Subscale Sukhoi was flown through a variety of high angle of attack maneuvers, specifically unpowered aggravated stalls, descending harriers, walls, and wing rock flight, during which flight data was recorded by the sensor data acquisition system. The flight data recorded during the maneuvers was processed to produce flight path trajectory plots, time histories and aircraft aerodynamic coefficient data. These plots showed unsteady aerodynamic effects exhibited by the aircraft. Among these results was one version of wing rock, where given a certain aircraft configuration with constant control surface inputs, the aircraft would wing rock with a constant frequency while the lift and drag coefficient oscillated with rapidly increasing then decreasing amplitudes, which has yet to be described in the literature.","Submission original under an indefinite embargo labeled 'Open Access'. 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The aircraft was instrumented with a custom sensor data acquisition system that allowed the motion and control inputs of the aircraft to be captured at a rate of 100 Hz. During the spring, summer, and fall of 2015, the UIUC Subscale Sukhoi was flown through a variety of high angle of attack maneuvers, specifically unpowered aggravated stalls, descending harriers, walls, and wing rock flight, during which flight data was recorded by the sensor data acquisition system. The flight data recorded during the maneuvers was processed to produce flight path trajectory plots, time histories and aircraft aerodynamic coefficient data. These plots showed unsteady aerodynamic effects exhibited by the aircraft. Among these results was one version of wing rock, where given a certain aircraft configuration with constant control surface inputs, the aircraft would wing rock with a constant frequency while the lift and drag coefficient oscillated with rapidly increasing then decreasing amplitudes, which has yet to be described in the literature.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2016-03-02 without embargo terms","The student, Or Dantsker, accepted the attached license on 2015-12-11 at 12:02.","The student, Or Dantsker, submitted this Thesis for approval on 2015-12-11 at 12:46.","This Thesis was approved for publication on 2015-12-11 at 14:14.","DSpace SAF Submission Ingestion Package generated from Vireo submission #8910 on 2016-03-02 at 12:50:57","Made available in DSpace on 2016-03-02T19:34:12Z (GMT). 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