{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/97452"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/97452","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Analysis of fountain effect for tiltrotor configuration using computational fluid simulation and experimental method","abstract":"The study involves a tiltrotor’s wing/rotor configuration design to properly test the model in both hover flight condition and crosswind condition replicated in the wind tunnel. To record data, a subsonic wind tunnel was utilized to test the wing/rotor configuration in different conditions of freestream velocity of V_∞=10, 15, and 20 m/s, the blade pitch angle of θ=5°, 10°, and 15°, and across a range of crosswind angles of β= 0°-90°. Post-processing of the obtained data was performed to interpret flow interactions between the rotor and wing in crosswind flight conditions and influences on the fountain effect. Further, a CFD simulation tool was used for comparison to these experiments. Also, a PIV experiment was performed to visualize the fountain effect’s flow structure, which occurred on the wing in the hover flight condition. A series of wind tunnel tests performed indicated that lift coefficients of the wind tunnel tests and CFD results closely replicate each other’s results for crosswind angles lower than 60°. Therefore, it can be stated that the URANS-based CFD methodology can simulate the tiltrotor’s wing/rotor configuration performance for flight conditions of lower crosswind angles, ideally from 0° to 45° for this particular study. Performing flow visualizations for crosswind flight conditions of lower crosswind angles indicated that the fountain effect is present in the hover flight condition. Then, the effect diminishes in the freestream flight condition. No significant change for thrust coefficient occurs. An induced flow beneath the rotor on the downstream side was observed to occur. Consequently, the thrust coefficient drops, indicating a performance decrease in higher crosswind angles.","abstract_html":"The study involves a tiltrotor’s wing/rotor configuration design to properly test the model in both hover flight condition and crosswind condition replicated in the wind tunnel. To record data, a subsonic wind tunnel was utilized to test the wing/rotor configuration in different conditions of freestream velocity of V_∞=10, 15, and 20 m/s, the blade pitch angle of θ=5°, 10°, and 15°, and across a range of crosswind angles of β= 0°-90°. Post-processing of the obtained data was performed to interpret flow interactions between the rotor and wing in crosswind flight conditions and influences on the fountain effect. Further, a CFD simulation tool was used for comparison to these experiments. Also, a PIV experiment was performed to visualize the fountain effect’s flow structure, which occurred on the wing in the hover flight condition. A series of wind tunnel tests performed indicated that lift coefficients of the wind tunnel tests and CFD results closely replicate each other’s results for crosswind angles lower than 60°. Therefore, it can be stated that the URANS-based CFD methodology can simulate the tiltrotor’s wing/rotor configuration performance for flight conditions of lower crosswind angles, ideally from 0° to 45° for this particular study. Performing flow visualizations for crosswind flight conditions of lower crosswind angles indicated that the fountain effect is present in the hover flight condition. Then, the effect diminishes in the freestream flight condition. No significant change for thrust coefficient occurs. An induced flow beneath the rotor on the downstream side was observed to occur. Consequently, the thrust coefficient drops, indicating a performance decrease in higher crosswind angles.","abstract_has_math":false,"creators":["Hong, Je Won"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"M.S.","degree_level":"Thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["Ansell, Phillip J."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2017,"date_issued":"2017-08-10T19:15:59Z","date_published":"2017-08-10T19:15:59Z","updated_at":"2026-07-22T22:24:34Z","subjects":["Tiltrotor","Fountain effect","Subsonic","Rotorcraft","Aerodynamics"],"languages":["en"],"rights":["Copyright 2017 Je Won Hong"],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/97452","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Ansell, Phillip J."]},{"key":"dc:creator","label":"Author","values":["Hong, Je Won"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2017-08-10T19:15:59Z","2017-04-25","2017-05"]},{"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":["Tiltrotor","Fountain effect","Subsonic","Rotorcraft","Aerodynamics"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2017 Je Won Hong"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["http://hdl.handle.net/2142/97452"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["The study involves a tiltrotor’s wing/rotor configuration design to properly test the model in both hover flight condition and crosswind condition replicated in the wind tunnel. To record data, a subsonic wind tunnel was utilized to test the wing/rotor configuration in different conditions of freestream velocity of V_∞=10, 15, and 20 m/s, the blade pitch angle of θ=5°, 10°, and 15°, and across a range of crosswind angles of β= 0°-90°. Post-processing of the obtained data was performed to interpret flow interactions between the rotor and wing in crosswind flight conditions and influences on the fountain effect. Further, a CFD simulation tool was used for comparison to these experiments. Also, a PIV experiment was performed to visualize the fountain effect’s flow structure, which occurred on the wing in the hover flight condition. A series of wind tunnel tests performed indicated that lift coefficients of the wind tunnel tests and CFD results closely replicate each other’s results for crosswind angles lower than 60°. Therefore, it can be stated that the URANS-based CFD methodology can simulate the tiltrotor’s wing/rotor configuration performance for flight conditions of lower crosswind angles, ideally from 0° to 45° for this particular study. Performing flow visualizations for crosswind flight conditions of lower crosswind angles indicated that the fountain effect is present in the hover flight condition. Then, the effect diminishes in the freestream flight condition. No significant change for thrust coefficient occurs. An induced flow beneath the rotor on the downstream side was observed to occur. Consequently, the thrust coefficient drops, indicating a performance decrease in higher crosswind angles.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2017-08-10 without embargo terms","The student, Je Won Hong, accepted the attached license on 2017-04-24 at 12:00.","The student, Je Won Hong, submitted this Thesis for approval on 2017-04-24 at 12:03.","This Thesis was approved for publication on 2017-04-25 at 17:31.","DSpace SAF Submission Ingestion Package generated from Vireo submission #11007 on 2017-08-10 at 13:45:38","Made available in DSpace on 2017-08-10T19:15:59Z (GMT). No. of bitstreams: 2 HONG-THESIS-2017.pdf: 3782121 bytes, checksum: 71c0aacb6d39a140a36e3528d00e4b8f (MD5) LICENSE.txt: 4208 bytes, checksum: a76de2b49746c54a6cc54411568d972e (MD5) Previous issue date: 2017-04-25"]},{"key":"dc:format","label":"Dc Format","values":["application/pdf"]},{"key":"dc:title","label":"Title","values":["Analysis of fountain effect for tiltrotor configuration using computational fluid simulation and experimental method"]}]}],"canonical_facts":{"dc:contributor":["Ansell, Phillip J."],"dc:creator":["Hong, Je Won"],"dc:date":["2017-08-10T19:15:59Z","2017-04-25","2017-05"],"dc:description":["The study involves a tiltrotor’s wing/rotor configuration design to properly test the model in both hover flight condition and crosswind condition replicated in the wind tunnel. To record data, a subsonic wind tunnel was utilized to test the wing/rotor configuration in different conditions of freestream velocity of V_∞=10, 15, and 20 m/s, the blade pitch angle of θ=5°, 10°, and 15°, and across a range of crosswind angles of β= 0°-90°. Post-processing of the obtained data was performed to interpret flow interactions between the rotor and wing in crosswind flight conditions and influences on the fountain effect. Further, a CFD simulation tool was used for comparison to these experiments. Also, a PIV experiment was performed to visualize the fountain effect’s flow structure, which occurred on the wing in the hover flight condition. A series of wind tunnel tests performed indicated that lift coefficients of the wind tunnel tests and CFD results closely replicate each other’s results for crosswind angles lower than 60°. Therefore, it can be stated that the URANS-based CFD methodology can simulate the tiltrotor’s wing/rotor configuration performance for flight conditions of lower crosswind angles, ideally from 0° to 45° for this particular study. Performing flow visualizations for crosswind flight conditions of lower crosswind angles indicated that the fountain effect is present in the hover flight condition. Then, the effect diminishes in the freestream flight condition. No significant change for thrust coefficient occurs. An induced flow beneath the rotor on the downstream side was observed to occur. Consequently, the thrust coefficient drops, indicating a performance decrease in higher crosswind angles.","Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2017-08-10 without embargo terms","The student, Je Won Hong, accepted the attached license on 2017-04-24 at 12:00.","The student, Je Won Hong, submitted this Thesis for approval on 2017-04-24 at 12:03.","This Thesis was approved for publication on 2017-04-25 at 17:31.","DSpace SAF Submission Ingestion Package generated from Vireo submission #11007 on 2017-08-10 at 13:45:38","Made available in DSpace on 2017-08-10T19:15:59Z (GMT). No. of bitstreams: 2 HONG-THESIS-2017.pdf: 3782121 bytes, checksum: 71c0aacb6d39a140a36e3528d00e4b8f (MD5) LICENSE.txt: 4208 bytes, checksum: a76de2b49746c54a6cc54411568d972e (MD5) Previous issue date: 2017-04-25"],"dc:format":["application/pdf"],"dc:identifier":["http://hdl.handle.net/2142/97452"],"dc:language":["en"],"dc:rights":["Copyright 2017 Je Won Hong"],"dc:subject":["Tiltrotor","Fountain effect","Subsonic","Rotorcraft","Aerodynamics"],"dc:title":["Analysis of fountain effect for tiltrotor configuration using computational fluid simulation and experimental method"],"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":"2026-07-22T22:24:34Z"}