Work continues on the projects of developing general aviation wings which can be laterally controlled into and through the stall. In 1989 a paper was presented which suggested that lateral control of a wing, and possibly additional lift at angles of attack above stall, could be obtained by use of hinged control surfaces at the leading-edge near the wing tips. This idea was pursued using a flow visualization model in the water tunnel and a reflection plane wind tunnel model. Both models used a modified NFL airfoil section and leading-edge and trailing-edge ailerons. The wind tunnel tests included both force and pressure distribution tests. A summary of these results is presented as well as outline of wing tip surveys currently going on in the water tunnels.


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    Title :

    Experimental Studies of General Aviation Wings at High Angles of Attack (Abstract Only)


    Contributors:

    Publication date :

    1991


    Size :

    1 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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