Lateral Stability and Control of a Tailless Aircraft Configuration
2009 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 46, no 6, 2161-2164 p.Article in journal (Refereed) Published
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.
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
IdentifiersURN: urn:nbn:se:kth:diva-19044DOI: 10.2514/1.41092ISI: 000272722300033ScopusID: 2-s2.0-73849083421OAI: oai:DiVA.org:kth-19044DiVA: diva2:337091
QC 201005252010-08-052010-08-052012-03-15Bibliographically approved