W.A. Agenbach

A generic low speed wind-tunnel flutter model was designed and manufactured, calibrated and wind-tunnel tested. The model will be used as a test vehicle for the study of active flutter suppression and active gust load alleviation. The design process included a parametric study to determine the influences of various design parameter changes on the flutter characteristics. Basic trends were noted and a final theoretical set of design parameters was selected to which the mechanical design and calibration were· tailored. The wind-tunnel tests were performed to verify the design goals and final theoretical flutter predictions. The model was sucessfully tested up to the flutter point and recovered.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 6 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.513-518; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991