A low-aspect-ratio, low-Reynolds-number membrane wing has been identified as a viable platform for micro air vehicle applications. Desirable flying qualities include high lift and larger stability margins. Several challenges are associated with the numerical modeling of such a wing, including highly three-dimensional flows, separation bubbles, and nonlinear membrane behavior. A thorough model validation and system identification effort is therefore required. A novel experimental setup integrates a wind tunnel with a visual image correlation system for simultaneous measurement of wing displacements, strains, and aerodynamic loads. These three metrics are used for a direct comparison of numerical and experimental data for both pre- and poststall angles of attack. Suitable correspondence is demonstrated for moderate angles of attack; methods for increasing the model fidelity can be made for angles with poor predictive capability. Computed flow structures reveal further information concerning the aeroelastic behavior of membrane wings.
Static aeroelastic model validation of membrane micro air vehicle wings
Statische aeroelastisches Modellvalidierung von Membran-Mikro-Flugzeugflügeln
AIAA Journal (online) ; 45 , 12 ; 2828-2837
2007
10 Seiten, 22 Bilder, 1 Tabelle, 19 Quellen
Article (Journal)
English
Tragfläche (Aerodynamik) , Reynolds-Zahl , Aspektverhältnis , Membrantechnik , Flugeigenschaft , numerische Strömungssimulation , dreidimensionale Darstellung , nichtlineares System , Validierung , Windkanalprüfung , Aerodynamik , Belastungsbereich , Verschiebung , Mikrosystemtechnik , Dehnungsmessgerät , Finite-Elemente-Methode
Static Aeroelastic Model Validation of Membrane Micro Air Vehicle Wings
Online Contents | 2007
|Static Aeroelastic Model Validation of Membrane Micro Air Vehicle Wings AIAA Paper
British Library Conference Proceedings | 2007
|Aeroelastic Analysis of Membrane Wings
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