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Self-induced roll oscillations of low-aspect-ratio rectangular wingsExperimental investigation of small aspect ratio rectangular wings mounted on a free-to-roll sting balance indicated that self-induced roll oscillations are possible when the aspect ratio of such wings is less than 0.5. The oscillations are probably driven by the periodic changes in the location and strength of the side edge vortices, as it has been shown for the 'wing rock' motion of delta wings, where similar changes in the leading edge vortex strength and position cause the roll oscillations. During the roll oscillation cycle the roll angle, normal force, and the side force were recorded and presented for three wings with aspect ratios of 0.25, 0.35, and 0.47. This data indicates that the lift loss during roll oscillations of rectangular wings is less than what was measured for similar delta wings. Also, the flow field of such slender rectangular wings at high angles of attack is more complicated due to the additional leading edge vortex, when compared with the flow field over slender delta wings.
Document ID
19900058096
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Levin, Daniel
(NASA Ames Research Center Moffett Field, CA, United States)
Katz, Joseph
(San Diego State University CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 90-2811
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference
Location: Portland, OR
Country: United States
Start Date: August 20, 1990
End Date: August 22, 1990
Accession Number
90A45151
Funding Number(s)
CONTRACT_GRANT: NCC2-458
Distribution Limits
Public
Copyright
Other

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