Exploratory tests have been conducted in the NASA-Langley Research Center's 12-Foot Low-Speed wind Tunnel to evaluate the application of wing-leading-edge devices on the stall-departure and spin resistance characteristics of a 1/6-scale model of a T-tail general-aviation aircraft. The model was force tested with an internal strain-gauge balance to obtain aerodynamic data on the complete configuration and with a separate wing balance to obtain aerodynamic data on the outer portion of the wing. The addition of the outboard leading-edge droop eliminated the abrupt stall of the windtip and maintained or increased the resultant-force coefficient up to about alpha = 32 degrees. This change in slope of the resultant-force coefficient curve with angle of attack has been shown to be important for eliminating autorotation and for providing spin resistance.


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    Title :

    Wind-Tunnel Investigation of Effects of Wing-Leading-Edge Modifications on the High Angle-of-Attack Characteristics of a T-Tail Low-Wing General-Aviation Aircraft


    Contributors:
    E. R. White (author)

    Publication date :

    1982


    Size :

    24 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English