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Design of an Aeroelastic Composite Wing Wind Tunnel Model.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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The USAF planned to participate in a parametric study investigating the effects of composite lamina fiber orientation on control reversal for various wingfin configurations. Only recently have complete wings, stabilizers, and control surfaces been fabricated from this material and a careful parametric study of aeroelastic effects has not been undertaken. In support of this effort, this thesis involved testing a single aft-swept wing planform with full and partial span trailing edge lateral control surfaces in a subsonic wind tunnel and comparing the results with predictions rendered from simple computer modeling. Three identical planform and composite laminate plates were tested but with the entire laminate rotated to different angles relative to the elastic axis. The composite plates were covered with foam and fabric to create a symmetric airfoil. The entire design methodology and construction techniques employed are presented. The research includes computer subroutines for initial design and prediction of the aeroelastic characteristics of each proposed configuration in terms of deformed shape, control reversal, divergence, and flutter. Keywords Composites Aileron reversal Aileron effectiveness divergence Flutter Aeroelasticity Optimization wind tunnel.
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