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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Reduction of Stall-Spin Entry Tendencies Through Wing Aerodynamic Design


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    National Business Aircraft Meeting and Engineering Display ; 1976



    Publication date :

    1976-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English





    A method for localizing wing flow separation at stall to alleviate spin entry tendencies

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



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

    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