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Lateral Stability and Control of a Tailless Aircraft Configuration
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.ORCID iD: 0000-0003-2391-641X
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.

Place, publisher, year, edition, pages
2009. Vol. 46, no 6, 2161-2164 p.
Keyword [en]
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: urn:nbn:se:kth:diva-19044DOI: 10.2514/1.41092ISI: 000272722300033Scopus ID: 2-s2.0-73849083421OAI: oai:DiVA.org:kth-19044DiVA: diva2:337091
Note
QC 20100525Available from: 2010-08-05 Created: 2010-08-05 Last updated: 2017-12-12Bibliographically approved
In thesis
1. An experimental study on the stability and control of a tailless aircraft
Open this publication in new window or tab >>An experimental study on the stability and control of a tailless aircraft
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:nbn:se:kth:diva-11329 (URN)
Presentation
(English)
Opponent
Supervisors
Available from: 2009-10-27 Created: 2009-10-26 Last updated: 2010-10-29Bibliographically approved
2. Aerodynamics and lateral control of tailless aircraft
Open this publication in new window or tab >>Aerodynamics and lateral control of tailless aircraft
2012 (English)Doctoral thesis, comprehensive summary (Other academic)
Place, publisher, year, edition, pages
Stockholm: KTH Royal Institute of Technology, 2012. 72 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2011:93
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-91407 (URN)978-91-7501-272-8 (ISBN)
Public defence
2012-03-30, F3, Lindstedtsvägen 26, KTH, Stockholm, 13:00 (English)
Opponent
Supervisors
Note
QC 20120315Available from: 2012-03-15 Created: 2012-03-14 Last updated: 2012-03-15Bibliographically approved

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Ringertz, Ulf

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