Detailed mean flow measurements were obtained at stations up to thirty chordlengths downstream in an airfoil trailing vortex using a yawhead pressure probe in the Virginia Tech Six-Foot Subsonic Tunnel. Mass injection at the wingtip was shown to hasten the vortex decay. A theoretical method has been developed to show the effect of wing circulation distribution on the structure of the outer portion of the vortex and excellent agreement with the experimental data is demonstrated. Experimental results indicate a much slower decay and higher tangential velocities than previously expected.


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    Titel :

    The farfield structure of aircraft wake turbulence.


    Beteiligte:

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1972 ; San Diego, CA


    Erscheinungsdatum :

    01.01.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    The farfield structure of aircraft wake turbulence

    MASON, W. / MARCHMAN, III, J. | AIAA | 1972



    Aircraft Wake Turbulence Avoidance

    W. A. Mcgowan | NTIS | 1971


    Aircraft wake turbulence avoidance

    Mcgowan, W. A. | NTRS | 1971


    AIRCRAFT WAKE TURBULENCE AWARENESS

    HERDER ANDREW J | Europäisches Patentamt | 2025

    Freier Zugriff