Small-scale Unmanned Aerial Vehicles (UAVs) have been used for decades and are increasing in number and effectiveness as aircraft, sensor and automation technologies mature. Since the demand for UAV platforms capable of performing multiple missions with enhanced performance is increasing, technologies as Circulation Control (CC), which is an active flow control technique that is used to achieve enhanced payload and aerodynamic efficiency, attracts the interest of the research community. This thesis describes the design, development,integration and testing (ground and flight testing) of a CC system capable to provide the required mass flow for a CC-based flight. Performance evaluation is conducted at individual component level and at overall system level using computational fluid dynamics analysis and experimental testing. The CC system, when integrated on-board the UAV, can achieve momentum coefficient of blowing (C) ranging from 0.009 to 0.05 depending on the application. Flight testing results validate the performance of the system and indicate that CC can be applied effectively on small-scale UAVs, overcoming space and power limitations.
","abstract_html":"<p>Small-scale Unmanned Aerial Vehicles (UAVs) have been used for decades and are increasing in number and effectiveness as aircraft, sensor and automation technologies mature. Since the demand for UAV platforms capable of performing multiple missions with enhanced performance is increasing, technologies as Circulation Control (CC), which is an active flow control technique that is used to achieve enhanced payload and aerodynamic efficiency, attracts the interest of the research community. This thesis describes the design, development,integration and testing (ground and flight testing) of a CC system capable to provide the required mass flow for a CC-based flight. Performance evaluation is conducted at individual component level and at overall system level using computational fluid dynamics analysis and experimental testing. The CC system, when integrated on-board the UAV, can achieve momentum coefficient of blowing (C) ranging from 0.009 to 0.05 depending on the application. Flight testing results validate the performance of the system and indicate that CC can be applied effectively on small-scale UAVs, overcoming space and power limitations.</p>","abstract_has_math":false,"creators":["Saka, Pranith Chander"],"institution":null,"degree_name":"M.S.","degree_level":"Masters Thesis","degree_discipline":null,"degree_department":null,"school":null,"contributors":["Kimon P. Valavanis, Ph.D.","Matthew J. Rutherford, Ph.D.","Corinne Lengsfeld"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2016,"date_issued":"2016-01-01T08:00:00Z","date_published":"2016-01-01T08:00:00Z","updated_at":"2026-07-24T02:02:45Z","subjects":["Air supply system","Unmanned circulation control aerial vehicle","Engineering"],"languages":["en"],"rights":["Copyright is held by the author. User is responsible for all copyright compliance.
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"],"dc:subject":["Air supply system","Unmanned circulation control aerial vehicle","Engineering"],"dc:title":["Design and Development of an Air Supply System for an Unmanned Circulation Control Aerial Vehicle"],"thesis:degree_level":["Masters Thesis"],"thesis:degree_name":["M.S."]},"updated_at":"2026-07-24T02:02:45Z"}