22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-4.6.2

DESIGN AND QUALIFICATION CONCEPTS FOR FLEXIBLE WIND TUNNEL WING MODELS

M. Kämpchen , W. Jung , A. Dafnis , H. G. Reimerdes
Department of Aerospace Structures - LightWeight Construction, RWTH Aachen

Keywords: wind tunnel test, flexible wing model, aeroelasticity, structural concepts, measurement techniques

Flexible wing models are used to examine aerostructural dynamical, aeroelastical and flight mechanical problems. Furthermore currently elastic models are being used to validate coupled software for direct simulation of flow-structure-interaction, particularly in the subsonic (start, landing) and in the transsonic region (mid-cruise). Sufficient deformation data should be made available for the wing models within the operating limits of the respective wind tunnels, without overstepping the linear-elastic region of the material. For the theoretical layout of the flexible, load carrying structure of the wing models, special software has been developed under consideration of the properties of open and closed beamsections and geometric non-linearities (caused by large wing deflections, following forces). The effort taken in technical measurement (for example interface load information at the clamping fixture, strain gauges, acceleration sensors, pressure sensors) to describe the static and dynamic structural behaviour under wind-on as well as wind-off conditions is outlined. Furthermore, methods of wing qualification are elaborated on. Experimental data is presented for a comparison with theoretical results obtained by direct simulation (computational aeroelasticity) methods.

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