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Aeroelastic tailoring for oblique wing lateral trimComposite material aeroelastic tailoring is presently explored as a means for the correction of the roll trim imbalance of oblique-wing aircraft configurations. The concept is demonstrated through the analysis of a realistic oblique wing by a static aeroelastic computational procedure encompassing the full potential transonic aerodynamic code FLO22 and a Ritz structural plate program that models the stiffness due to symmetrical-but-unbalanced composite wing skins. Results indicate that asymetric composite tailoring reduces the aileron deflection needed for roll equilibrium, and reduces control surface hinge moment and drag. Wing skin stresses are, however, very high.
Document ID
19880044993
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bohlmann, Jonathan D.
(Purdue Univ. West Lafayette, IN, United States)
Weisshaar, Terrence A.
(Purdue University West Lafayette, IN, United States)
Eckstrom, Clinton V.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 88-2263
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference
Location: Williamsburg, VA
Country: United States
Start Date: April 18, 1988
End Date: April 20, 1988
Sponsors: Structures
Accession Number
88A32220
Funding Number(s)
CONTRACT_GRANT: NAG1-372
Distribution Limits
Public
Copyright
Other

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