H. Korsch, A. Dafnis, H.-G. Reimerdes

A highly flexible straight wing model with a supercritical airfoil has been designed and manufactured for the investigation of aero-structural equilibrium configurations and aerodynamic damping at various flow velocities in a subsonic wind tunnel. The main objective is to provide fundamental experimental data for the validation of new Computational Aeroelasticity design tools developed at Aachen University. The wing model used here is characterised by a zero torsional wing tip deformation at the design point and a static unbalance. The sizing and construction, the measurement technique and the tests in laboratory which yield the statical and dynamical identification parameters of the wing model structure under wind-off condition will be presented. Results from the wing model qualification and the wind tunnel tests will be discussed especially considering the design criteria. For the latter the damping behaviour of the wing model under wind-on conditions will be presented.

International Forum on Aeroelasticity and Structural Dynamics, 2005, München

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

DGLR-Bericht, 2005, 2005-04, International Forum on Aeroelasticity and Structural Dynamics 2005; S.1-12; 2005; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

in getr. Zählung;

wind tunnel tests, fluid structure interaction

Bibliothek

2005