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An experimental study on the stability and control of a tailless aircraft
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering. (Flight dynamics)
2009 (English)Licentiate thesis, comprehensive summary (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH , 2009. , 25 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2009:64
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:kth:diva-11329OAI: oai:DiVA.org:kth-11329DiVA: diva2:274066
Presentation
(English)
Opponent
Supervisors
Available from: 2009-10-27 Created: 2009-10-26 Last updated: 2010-10-29Bibliographically approved
List of papers
1. Aerodynamics of a Tailless Wind Tunnel Model
Open this publication in new window or tab >>Aerodynamics of a Tailless Wind Tunnel Model
2009 (English)Report (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH, 2009
Series
Trita-AVE, ISSN 1651-7660 ; 2009:72
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-25761 (URN)
Note
QC 20101029Available from: 2010-10-29 Created: 2010-10-29 Last updated: 2012-03-15Bibliographically approved
2. Lateral Stability and Control of a Tailless Aircraft Configuration
Open this publication in new window or tab >>Lateral Stability and Control of a Tailless Aircraft Configuration
2009 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 46, no 6, 2161-2164 p.Article in journal (Refereed) Published
Abstract [en]

The aerodynamics of a generic aircraft configuration known as Swing was investigated. The configuration used had two trailing-edge flaps on each wing used for control around all three stability axes included pitch, roll, and yaw. Tests are done in the low-speed wind tunnel L2000 at a freestream velocity of 30 m/s corresponding to a Reynolds number of 6.9 · 105 was applied. A NACA-66009 airfoil was used for the wing, and the outer wing section was twisted up 5° around the leading-edge point of the wing. Asymmetric deflections with the same amplitude for both flaps on each wing were applied for roll control. The deflection of the flaps was recorded with a motion capture system. The infrared light was emitted from four cameras and the light was reflected back to the cameras with a scan rate of 100 Hz and the system computed the distance to the markers. The results revealed that a sudden increase in pitch moment were observed at angles of attack above 10° and the flaps deflected with the same amplitude.

Keyword
Aircraft configurations, Angles of attack, Free-stream velocity, Infrared light, Lateral stability, Leading edge, Low-speed wind tunnel, Motion capture system, Pitch moment, Scan rates, Tailless aircraft, Trailing-edge flaps, Wing section
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-19044 (URN)10.2514/1.41092 (DOI)000272722300033 ()2-s2.0-73849083421 (Scopus ID)
Note
QC 20100525Available from: 2010-08-05 Created: 2010-08-05 Last updated: 2017-12-12Bibliographically approved
3. Lateral Control of a Tailless Aircraft Configuration
Open this publication in new window or tab >>Lateral Control of a Tailless Aircraft Configuration
2009 (English)Report (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH, 2009
Series
Trita-AVE, ISSN 1651-7660 ; 2009:73
National Category
Vehicle Engineering
Identifiers
urn:nbn:se:kth:diva-25762 (URN)
Note
QC 20101029Available from: 2010-10-29 Created: 2010-10-29 Last updated: 2010-10-29Bibliographically approved

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CiteExportLink to record
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Citation style
  • apa
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More styles
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Output format
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