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.


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    Title :

    Static aeroelastic model validation of membrane micro air vehicle wings


    Additional title:

    Statische aeroelastisches Modellvalidierung von Membran-Mikro-Flugzeugflügeln


    Contributors:

    Published in:

    AIAA Journal (online) ; 45 , 12 ; 2828-2837


    Publication date :

    2007


    Size :

    10 Seiten, 22 Bilder, 1 Tabelle, 19 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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