{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/85091"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/85091","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Reentry Vehicle Aerodynamics and Control at Very High Angle of Attack","abstract":"In recent flight tests the X-38 reentry test vehicle spins during the deployment of the drogue parachute. An experimental aerodynamic study has been conducted at the University of Illinois using a scale model of the X-38 to explore the cause of this problem. A six-component sting balance was used to measure the forces and moments on the 4.7% wind tunnel model at angles of attack from -7° to 95°. In addition, surface pressure taps and flow visualization techniques were utilized to determine the forebody pressures and surface flowfield on the model. The effect of Reynolds number and boundary-layer state were also examined. The investigation suggests that the spinning under the drogue parachute was caused by asymmetric vortex formation. At angles of attack between 75° and 90° vortex asymmetry developed in all of the cases without separation geometrically fixed. This flow asymmetry produced large side forces and yawing moments. The Reynolds number effect and the effect of the boundary-layer state were noticeable, but did not greatly change the side force and yawing moment characteristics of the model. The micro-geometry of the model had a large effect on the side force generated by the vortex positioning. The effects of forced oscillations were also examined and it was determined that the side forces were still present during the oscillations. Control of the vortices and side forces was obtained by applying strakes to the side of the forebody of the model.","abstract_html":"In recent flight tests the X-38 reentry test vehicle spins during the deployment of the drogue parachute. An experimental aerodynamic study has been conducted at the University of Illinois using a scale model of the X-38 to explore the cause of this problem. A six-component sting balance was used to measure the forces and moments on the 4.7% wind tunnel model at angles of attack from -7° to 95°. In addition, surface pressure taps and flow visualization techniques were utilized to determine the forebody pressures and surface flowfield on the model. The effect of Reynolds number and boundary-layer state were also examined. The investigation suggests that the spinning under the drogue parachute was caused by asymmetric vortex formation. At angles of attack between 75° and 90° vortex asymmetry developed in all of the cases without separation geometrically fixed. This flow asymmetry produced large side forces and yawing moments. The Reynolds number effect and the effect of the boundary-layer state were noticeable, but did not greatly change the side force and yawing moment characteristics of the model. The micro-geometry of the model had a large effect on the side force generated by the vortex positioning. The effects of forced oscillations were also examined and it was determined that the side forces were still present during the oscillations. Control of the vortices and side forces was obtained by applying strakes to the side of the forebody of the model.","abstract_has_math":false,"creators":["Merret, Jason Michael"],"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":"2015-09-25T22:34:24Z","date_published":"2015-09-25T22:34:24Z","updated_at":"2026-07-22T22:26:24Z","subjects":["Engineering, Aerospace"],"languages":["eng"],"rights":[],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["(MiAaPQ)AAI3160924"],"render_values":[{"text":"(MiAaPQ)AAI3160924","href":null,"code":true}]}]},"links":{"outbound_url":"http://hdl.handle.net/2142/85091","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":["Merret, Jason Michael"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2015-09-25T22:34:24Z","10000-01-01","2004"]},{"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/2142/85091","(MiAaPQ)AAI3160924"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["In recent flight tests the X-38 reentry test vehicle spins during the deployment of the drogue parachute. An experimental aerodynamic study has been conducted at the University of Illinois using a scale model of the X-38 to explore the cause of this problem. A six-component sting balance was used to measure the forces and moments on the 4.7% wind tunnel model at angles of attack from -7° to 95°. In addition, surface pressure taps and flow visualization techniques were utilized to determine the forebody pressures and surface flowfield on the model. The effect of Reynolds number and boundary-layer state were also examined. The investigation suggests that the spinning under the drogue parachute was caused by asymmetric vortex formation. At angles of attack between 75° and 90° vortex asymmetry developed in all of the cases without separation geometrically fixed. This flow asymmetry produced large side forces and yawing moments. The Reynolds number effect and the effect of the boundary-layer state were noticeable, but did not greatly change the side force and yawing moment characteristics of the model. The micro-geometry of the model had a large effect on the side force generated by the vortex positioning. The effects of forced oscillations were also examined and it was determined that the side forces were still present during the oscillations. Control of the vortices and side forces was obtained by applying strakes to the side of the forebody of the model.","Made available in DSpace on 2015-09-25T22:34:24Z (GMT). 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An experimental aerodynamic study has been conducted at the University of Illinois using a scale model of the X-38 to explore the cause of this problem. A six-component sting balance was used to measure the forces and moments on the 4.7% wind tunnel model at angles of attack from -7° to 95°. In addition, surface pressure taps and flow visualization techniques were utilized to determine the forebody pressures and surface flowfield on the model. The effect of Reynolds number and boundary-layer state were also examined. The investigation suggests that the spinning under the drogue parachute was caused by asymmetric vortex formation. At angles of attack between 75° and 90° vortex asymmetry developed in all of the cases without separation geometrically fixed. This flow asymmetry produced large side forces and yawing moments. The Reynolds number effect and the effect of the boundary-layer state were noticeable, but did not greatly change the side force and yawing moment characteristics of the model. The micro-geometry of the model had a large effect on the side force generated by the vortex positioning. The effects of forced oscillations were also examined and it was determined that the side forces were still present during the oscillations. Control of the vortices and side forces was obtained by applying strakes to the side of the forebody of the model.","Made available in DSpace on 2015-09-25T22:34:24Z (GMT). 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