23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-4.1.2

STABILITY ANALYSIS IN THE TIME-DOMAIN APPLIED TO ADAPTIVE TRANSPORT-AIRCRAFT WINGS

W. Send, R. Voss
DLR, Germany

Keywords: aeroelastic stability, coupling fluid/structure, contour bump

A procedure for coupling fluid and structure is described, in which the structure is given by a Finite Elements model, and the fluid is computed with a flow solver for compressible flow. The tool is applied to the wing model of a modern transport aircraft, which is equipped with a small contour modification on the upper surface for drag reduction in the shock region. The aeroelastic stability is investigated in comparison to the original contour shape. Particular emphasis is laid on a proper mapping of the flow quantities into the structure and vice versa.

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