25th Congress of International Council of the Aeronautical Sciences, 3 - 8 September 2006, Hamburg, Germany
Paper ICAS 2006-4.9.4

NUMERICAL SIMULATION OF C-141 LOWER WING PANELS WITH AND WITHOUT SIMULATED EXFOLIATION CORROSION UNDER COMPRESSION

G. Li, G. Shi, M. Yanishevsky
National Research Council/IAR, Canada

Keywords: Finite element methods, post-buckling, stiffened wing panel

In-plane compression studies of two stiffened C-141 lower wing panels were carried out both experimentally and numerically. One panel was pristine and the other had simulated damage. Details and discussions on the maximum compression load, strain and stress results obtained from the experimental and 3D numerical results were presented.

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