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Aeroelastic stability and control of an oblique wing - Wind tunnel experimentsResults are presented for wind tunnel tests of an elastic wing model to verify the theoretical predictions for the aeroelastic instability of an oblique wing. The model wing has an elliptic planform of 10 to 1 axis ratio and a symmetrical airfoil section of 7-1/2% thickness/chord ratio. The wing is of wood and as may be seen in the photographs presented, slack wires are used to limit the amplitude of unstable motions. The fuselage is mounted on bearings permitting freedom of roll, but provision is made to clamp the fuselage for some of the tests. It is found that freedom in roll increases the dynamic pressure at which aeroelastic instability first appears. With the model free in roll, the effectiveness of the ailerons in maintaining trim is not noticeably affected by passage through the speed at which the wing would become unstable if clamped.
Document ID
19760064234
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Jones, R. T.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
October 1, 1976
Publication Information
Publication: Journal of Aircraft
Volume: 13
Subject Category
Aircraft Stability And Control
Accession Number
76A47200
Distribution Limits
Public
Copyright
Other

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