An airplane stall proofing system utilizing a spoiler was investigated for application on a low wing airplane representative of typical general aviation aircraft. Tests of the full scale airplane were conducted in the NASA Langley 30 x 60 foot full scale wind tunnel. The test velocity was 86 feet per second, corresponding to a Reynolds number of 2.20 million. The stall proofing capability of the spoiler is shown and a theoretical approach to the design of the spoiler and analysis of the spoiler's contribution to the airplane's trim and longitudinal stability is verified. Controlled spoiler deployment in a narrow angle of attack range, 4 degrees, immediately preceding the stall angle will stall proof the airplane. The results also show some of the limitations of flight tests to determine spoiler deployment rate for good handling qualities.


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    Titel :

    Summary of Theoretical Considerations and Wind Tunnel Tests of an Aerodynamic Spoiler for Stall Proofing a General Aviation Airplane


    Beteiligte:

    Erscheinungsdatum :

    1982


    Format / Umfang :

    55 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch