{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/30943"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/30943","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Measurement of aerodynamic characteristics of MAVs using motion tracking","abstract":"Aerodynamic characteristics of Micro Air Vehicles (MAVs) is not well addressed in aeronautics literature, and more experimental data are required to help better understand the behavior of fixed-wing MAVs. In the current research, aerodynamic and stability characteristics of two MAVs were measured using a motion tracking system. Both the aircraft position and propeller rotation were tracked. The aircraft used were flat foam surface, highly aerobatic RC models. Tests were conducted for unpowered and powered flight conditions to assess the aerodynamic performance of a commercially manufactured Extra 300 3D and a custom-built Extra 260 with wingspans of 42.67 cm (16.8 in) and 41.27 cm (16.25 in), respectively. A comparison of theoretical calculations with experimental results was made for parameters such as the lift curve and neutral point location. The aircraft used in this research operated in a Reynolds number range of 20,000 to 30,000. Low Reynolds numbers effects that influence the aerodynamic characteristics and performance of the aircraft are discussed in this thesis. The behavior of MAVs in powered flight was analyzed by testing the Extra 300 3D over a range of propeller advance ratios (J = 0.3–1.0) with the propeller running at pre-determined speeds (RPM). A thrust model was developed for a commercially manufactured propeller, and the lift and drag characteristics of the aircraft was analyzed. The results indicate that the propeller induced flow influences the aerodynamic performance of the aircraft. Results indicate a delay in the onset of stall, an increase in the lift curve slope, and reduction in drag with decreasing advance ratios (J). The results show a myriad of interesting aerodynamic trends that are discussed.","abstract_html":"Aerodynamic characteristics of Micro Air Vehicles (MAVs) is not well addressed in aeronautics literature, and more experimental data are required to help better understand the behavior of fixed-wing MAVs. In the current research, aerodynamic and stability characteristics of two MAVs were measured using a motion tracking system. Both the aircraft position and propeller rotation were tracked. The aircraft used were flat foam surface, highly aerobatic RC models. Tests were conducted for unpowered and powered flight conditions to assess the aerodynamic performance of a commercially manufactured Extra 300 3D and a custom-built Extra 260 with wingspans of 42.67 cm (16.8 in) and 41.27 cm (16.25 in), respectively. A comparison of theoretical calculations with experimental results was made for parameters such as the lift curve and neutral point location. The aircraft used in this research operated in a Reynolds number range of 20,000 to 30,000. Low Reynolds numbers effects that influence the aerodynamic characteristics and performance of the aircraft are discussed in this thesis. The behavior of MAVs in powered flight was analyzed by testing the Extra 300 3D over a range of propeller advance ratios (J = 0.3–1.0) with the propeller running at pre-determined speeds (RPM). A thrust model was developed for a commercially manufactured propeller, and the lift and drag characteristics of the aircraft was analyzed. The results indicate that the propeller induced flow influences the aerodynamic performance of the aircraft. Results indicate a delay in the onset of stall, an increase in the lift curve slope, and reduction in drag with decreasing advance ratios (J). The results show a myriad of interesting aerodynamic trends that are discussed.","abstract_has_math":false,"creators":["Rao, Arjun"],"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":2012,"date_issued":"2012-05-22T00:17:27Z","date_published":"2012-05-22T00:17:27Z","updated_at":"2026-07-22T22:25:29Z","subjects":["Micro air vehicle (MAV)","Reynolds number","remote controlled (RC)","aircraft","airplane","model","Lift","drag","thrust","moment","stability","control","pitch","roll","yaw","weathercock","weathervane","motion tracking","motion capture","VICON","camera","wand","Re","lift curve","drag polar","propeller","Advanced Precision Composites (APC)","sport","E-flite","sideslip","static margin (SM)","axis","axes","PropellerScanner","airfoil","wing","lifting line theory","theory","experimental","Aerodynamics","calibration","noise","markers","Euler angles","longitudinal","lateral","advance ratio","density","data points","Extra 260","Extra 300 3D","glider","frequency","revolutions per minute (RPM)","body-fixed","Earth-fixed","transformation","rotation","matrix","filter","low-pass","finite difference","robust","lineqar","least-squares","parabolic","Uhlig","Selig","Rao"],"languages":["en"],"rights":["Copyright 2012 by Arjun Harsha Rao. All rights reserved."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"http://hdl.handle.net/2142/30943","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":["Rao, Arjun"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2012-05-22T00:17:27Z","2012-05"]},{"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":["Micro air vehicle (MAV)","Reynolds number","remote controlled (RC)","aircraft","airplane","model","Lift","drag","thrust","moment","stability","control","pitch","roll","yaw","weathercock","weathervane","motion tracking","motion capture","VICON","camera","wand","Re","lift curve","drag polar","propeller","Advanced Precision Composites (APC)","sport","E-flite","sideslip","static margin (SM)","axis","axes","PropellerScanner","airfoil","wing","lifting line theory","theory","experimental","Aerodynamics","calibration","noise","markers","Euler angles","longitudinal","lateral","advance ratio","density","data points","Extra 260","Extra 300 3D","glider","frequency","revolutions per minute (RPM)","body-fixed","Earth-fixed","transformation","rotation","matrix","filter","low-pass","finite difference","robust","lineqar","least-squares","parabolic","Uhlig","Selig","Rao"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["en"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 2012 by Arjun Harsha Rao. 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Tests were conducted for unpowered and powered flight conditions to assess the aerodynamic performance of a commercially manufactured Extra 300 3D and a custom-built Extra 260 with wingspans of 42.67 cm (16.8 in) and 41.27 cm (16.25 in), respectively. A comparison of theoretical calculations with experimental results was made for parameters such as the lift curve and neutral point location. The aircraft used in this research operated in a Reynolds number range of 20,000 to 30,000. Low Reynolds numbers effects that influence the aerodynamic characteristics and performance of the aircraft are discussed in this thesis. The behavior of MAVs in powered flight was analyzed by testing the Extra 300 3D over a range of propeller advance ratios (J = 0.3–1.0) with the propeller running at pre-determined speeds (RPM). A thrust model was developed for a commercially manufactured propeller, and the lift and drag characteristics of the aircraft was analyzed. The results indicate that the propeller induced flow influences the aerodynamic performance of the aircraft. Results indicate a delay in the onset of stall, an increase in the lift curve slope, and reduction in drag with decreasing advance ratios (J). The results show a myriad of interesting aerodynamic trends that are discussed.","Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2012-04-24T18:55:10Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 1 Rao_Arjun.pdf: 26485280 bytes, checksum: 57533ec1cfaa4abb31b2df8c9bf60717 (MD5)","Made available in DSpace on 2012-05-22T00:17:27Z (GMT). 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Tests were conducted for unpowered and powered flight conditions to assess the aerodynamic performance of a commercially manufactured Extra 300 3D and a custom-built Extra 260 with wingspans of 42.67 cm (16.8 in) and 41.27 cm (16.25 in), respectively. A comparison of theoretical calculations with experimental results was made for parameters such as the lift curve and neutral point location. The aircraft used in this research operated in a Reynolds number range of 20,000 to 30,000. Low Reynolds numbers effects that influence the aerodynamic characteristics and performance of the aircraft are discussed in this thesis. The behavior of MAVs in powered flight was analyzed by testing the Extra 300 3D over a range of propeller advance ratios (J = 0.3–1.0) with the propeller running at pre-determined speeds (RPM). A thrust model was developed for a commercially manufactured propeller, and the lift and drag characteristics of the aircraft was analyzed. 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All rights reserved."],"dc:subject":["Micro air vehicle (MAV)","Reynolds number","remote controlled (RC)","aircraft","airplane","model","Lift","drag","thrust","moment","stability","control","pitch","roll","yaw","weathercock","weathervane","motion tracking","motion capture","VICON","camera","wand","Re","lift curve","drag polar","propeller","Advanced Precision Composites (APC)","sport","E-flite","sideslip","static margin (SM)","axis","axes","PropellerScanner","airfoil","wing","lifting line theory","theory","experimental","Aerodynamics","calibration","noise","markers","Euler angles","longitudinal","lateral","advance ratio","density","data points","Extra 260","Extra 300 3D","glider","frequency","revolutions per minute (RPM)","body-fixed","Earth-fixed","transformation","rotation","matrix","filter","low-pass","finite difference","robust","lineqar","least-squares","parabolic","Uhlig","Selig","Rao"],"dc:title":["Measurement of aerodynamic characteristics of MAVs using motion tracking"],"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":"2026-07-22T22:25:29Z"}