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 degree angle of attack. It is hypothesized that his 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


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

    Kongress:

    Business Aircraft Meeting ; 1976 ; Wichita, KS, United States


    Erscheinungsdatum :

    1976-04-06


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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


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

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