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Aerodynamics and lateral control of tailless aircraft
KTH, School of Engineering Sciences (SCI), Aeronautical and Vehicle Engineering, Flight Dynamics.
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: urn:nbn:se:kth:diva-91407ISBN: 978-91-7501-272-8 (print)OAI: oai:DiVA.org:kth-91407DiVA: diva2:509961
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
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. Steady and unsteady pressure measurements on a swept-wing aircraft
Open this publication in new window or tab >>Steady and unsteady pressure measurements on a swept-wing aircraft
2011 (English)Report (Other academic)
Publisher
18 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2011:91
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-91404 (URN)
Note
To be submitted for publication. QC 20120315Available from: 2012-03-14 Created: 2012-03-14 Last updated: 2012-05-29Bibliographically approved
3. 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
4. Yaw control of a tailless aircraft configuration
Open this publication in new window or tab >>Yaw control of a tailless aircraft configuration
2010 (English)In: Journal of Aircraft, ISSN 0021-8669, E-ISSN 1533-3868, Vol. 47, no 5, 1807-1810 p.Article in journal (Refereed) Published
Abstract [en]

The yaw control of a tailless aircraft configuration is investigated. The four trailing-edge control surfaces are actuated using electrical servos which are controlled using a custom designed Ethernet interface. Measurements of the yaw moment due to sideslip and due to split flap deflections have been performed using a strain gauge balance for both sting configurations in order to estimate the sting interference effects. The mass moment of inertia J is obtained from a yaw ground vibration test using the yaw sting with a torsional spring installed. Dynamic stability is estimated by performing vibration tests in yaw with the torsional spring installed. The required control surface deflections can be large due to the low dynamic pressure when landing. The configuration uses only four flaps for simultaneous control around all three axes and necessary control surface deflections for pitch, roll and yaw need to be superimposed at all times.

National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-91400 (URN)10.2514/1.C031017 (DOI)000283206100034 ()2-s2.0-78049392997 (Scopus ID)
Note
QC 20120315Available from: 2012-03-14 Created: 2012-03-14 Last updated: 2017-12-07Bibliographically approved
5. High angle of attack and sideslip aerodynamics of a tailless aircraft
Open this publication in new window or tab >>High angle of attack and sideslip aerodynamics of a tailless aircraft
2011 (English)Report (Other academic)
Publisher
17 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2011:90
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-91405 (URN)
Note
QC 20120315Available from: 2012-03-14 Created: 2012-03-14 Last updated: 2012-03-15Bibliographically approved
6. Yaw departure and recovery of a tailless aircraft configuration
Open this publication in new window or tab >>Yaw departure and recovery of a tailless aircraft configuration
2011 (English)Report (Other academic)
Publisher
12 p.
Series
Trita-AVE, ISSN 1651-7660 ; 2011:92
National Category
Aerospace Engineering
Identifiers
urn:nbn:se:kth:diva-91406 (URN)
Note
Submitted for publication. QC 20120315Available from: 2012-03-14 Created: 2012-03-14 Last updated: 2012-03-15Bibliographically approved

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