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A Comprehensive Methodology for Design of a Circulation Control Small-Scale Unmanned Aircraft.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	A Comprehensive Methodology for Design of a Circulation Control Small-Scale Unmanned Aircraft./
作者:	Kanistras, Konstantinos.
面頁冊數:	1 online resource (171 pages)
附註:	Source: Dissertation Abstracts International, Volume: 77-11(E), Section: B.
Contained By:	Dissertation Abstracts International77-11B(E).
標題:	Aerospace engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9781339756530

A Comprehensive Methodology for Design of a Circulation Control Small-Scale Unmanned Aircraft.
Kanistras, Konstantinos.

A Comprehensive Methodology for Design of a Circulation Control Small-Scale Unmanned Aircraft. - 1 online resource (171 pages)

Source: Dissertation Abstracts International, Volume: 77-11(E), Section: B.

Thesis (Ph.D.)

Includes bibliographical references

This item is not available from ProQuest Dissertations & Theses.

Unmanned Aerial Vehicles (UAVs) have become increasingly prevalent and important for a wide spectrum of civilian and military operations. When focusing on small-scale fixed-wing UAVs, payload, power and energy requirements limit considerably their utilization and flexibility allowing them to complete only those specific missions they are designed for. Circulation Control (CC) is an active flow control method used to produce increased lift over the traditional systems (flaps, slats, etc...) currently in use. This dissertation focuses on the foundations of a comprehensive methodology from design to implementation and experimental testing of Coanda-based Circulation Control Wings (CCW) for unmanned aircraft. The research goes beyond the current state of the art by demonstrating the feasibility of CC as applied to small-scale UAVs. 2-D and 3-D wind tunnel tests at Mach numbers of 0.03, with momentum coefficients of blowing (Cmu) ranging from 0.0 to 0.3 are conducted. It is found that CC blowing is eeffective at all cases enabling the wing to achieve high lift-to-drag ratios and high lift augmentation during takeoff. The wind tunnel results indicate that upper slot blowing using CC can be effective for lift enhancement even at low blowing rates. Through flight testing it is confirmed that CC can be applied to small-scale UAVs resulting in significant runway reduction up to 53%. The technology described herein can be made suitable for use on commercial airliners, cargo planes and personal aerial vehicles because equipping these aircraft with cruise-efficient high-lift devices can give the user more valid runway choices at existing airports and help alleviate environmental noise problems near airports by allowing steeper climb-outs.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2018

Mode of access: World Wide Web

ISBN: 9781339756530Subjects--Topical Terms:

686400
Aerospace engineering.
Index Terms--Genre/Form:

554714
Electronic books.

A Comprehensive Methodology for Design of a Circulation Control Small-Scale Unmanned Aircraft.
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500 $a Advisers: Kimon P. Valavanis; Matthew J. Rutherford.
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504 $a Includes bibliographical references
506 $a This item is not available from ProQuest Dissertations & Theses.
520 $a Unmanned Aerial Vehicles (UAVs) have become increasingly prevalent and important for a wide spectrum of civilian and military operations. When focusing on small-scale fixed-wing UAVs, payload, power and energy requirements limit considerably their utilization and flexibility allowing them to complete only those specific missions they are designed for. Circulation Control (CC) is an active flow control method used to produce increased lift over the traditional systems (flaps, slats, etc...) currently in use. This dissertation focuses on the foundations of a comprehensive methodology from design to implementation and experimental testing of Coanda-based Circulation Control Wings (CCW) for unmanned aircraft. The research goes beyond the current state of the art by demonstrating the feasibility of CC as applied to small-scale UAVs. 2-D and 3-D wind tunnel tests at Mach numbers of 0.03, with momentum coefficients of blowing (Cmu) ranging from 0.0 to 0.3 are conducted. It is found that CC blowing is eeffective at all cases enabling the wing to achieve high lift-to-drag ratios and high lift augmentation during takeoff. The wind tunnel results indicate that upper slot blowing using CC can be effective for lift enhancement even at low blowing rates. Through flight testing it is confirmed that CC can be applied to small-scale UAVs resulting in significant runway reduction up to 53%. The technology described herein can be made suitable for use on commercial airliners, cargo planes and personal aerial vehicles because equipping these aircraft with cruise-efficient high-lift devices can give the user more valid runway choices at existing airports and help alleviate environmental noise problems near airports by allowing steeper climb-outs.
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