A helicopter tail rotor is required to provide yaw control and essentially that alone. However, it is expected to achieve that role when placed in an aerodynamically difficult location on the aircraft and to operate in a severe aerodynamic environment. This paper describes the pedal travel behaviour caused by aerodynamic interaction between the main rotor wake, the sideways velocity and subsequent forces generated by the tail boom noticed in Sea King helicopters, operating in extreme conditions during the Falklands war. Using earlier research which showed the effectiveness of a modification – a strake – to interrupt the air flow over the tail boom, conducts tests to examine the flow, the effects of the modification, and the side suction force. It also finds that the strake provides a simple and cost-effective solution to the problem.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    The tail boom strake


    Beteiligte:
    Adams, Mark (Autor:in) / Newman, Simon (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2004-04-01


    Format / Umfang :

    17 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    The tail boom strake

    Adams, Mark | Online Contents | 2004


    Development in helicopter tail boom strake applications in the US

    Wilson, John C. / Kelley, Henry L. / Donahue, Cynthia C. et al. | NTRS | 1988


    Development in Helicopter Tail Boom Strake Applications in the US

    J. C. Wilson / H. L. Kelley / C. C. Donahue et al. | NTIS | 1988


    Flight Characteristics Test of the UH-60A with Tail Boom Mounted Strake

    R. A. Lockwood / W. A. Kelly / R. W. Carson | NTIS | 1986