Results of recent wind tunnel tests and analyses are described which are aimed at helping to prevent spin entry after a stall by modifications to the aircraft wing. Simple add-on devices were utilized which modify the shape of the lift curve after stall, making it essentially flat to 30-40° angle of attack. It is hypothesized that this will greatly reduce the danger of spin entry. Further research will be aimed at laying a firmer theoretical and analytical basis for the approach and at incorporating the complete full scale airplane and its dynamics into the problem.


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    Titel :

    Reduction of Stall-Spin Entry Tendencies Through Wing Aerodynamic Design


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Kroeger, R. A. (Autor:in) / Feistel, T. W. (Autor:in)

    Kongress:

    National Business Aircraft Meeting and Engineering Display ; 1976



    Erscheinungsdatum :

    01.02.1976




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch





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    Feistel, T. W. / Anderson, S. B. / Kroeger, R. A. | NTRS | 1978



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    Feistel, T. W. / Anderson, S. B. / Kroeger, R. A. | NTRS | 1981


    Alleviation of Spin-Entry Tendencies through Localization of Wing-Flow Separation

    T. W. Feistel / S. B. Anderson / R. A. Kroeger | AIAA | 1981