Flight tests have been conducted to evaluate the effectiveness of a wing-tip vortex attenuating device, referred to as a spline. Vortex penetrations were made with a PA-28 behind a C-54 aircraft with and without wing-tip splines attached, and the resultant rolling acceleration was measured and related to the roll acceleration capability of the PA-28. Tests were conducted over a range of separation distances from about 5 n mi to less than 1 n mi. Preliminary results indicate that, with the splines installed, there was a significant reduction in the vortex-induced roll acceleration experienced by the PA-28 probe aircraft, and the distance at which the PA-28 roll control became ineffective was reduced from 2.5 n mi to less than 1 n mi. Although splines significantly reduced the C-54 rate of climb, the rates available with four engines were acceptable for this test program.


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    Titel :

    Results of full-scale vortex attenuation flight experiments


    Beteiligte:

    Kongress:

    Annual Symposium on Advancements in flight test engineering ; 1974 ; Anaheim, CA


    Erscheinungsdatum :

    1974-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Vortex attenuation flight experiments

    Barber, M. R. / Hastings, E. C., Jr. / Champine, R. A. et al. | NTRS | 1977


    Wake Vortex Attenuation Flight Tests: A Status Report

    Barber, Marvin R. / Tymczyszyn, Joseph J. | NTRS | 1981


    Wake vortex attenuation flight tests - A status report

    Barber, M. R. / Tymczyszyn, J. J. | NTRS | 1982



    Vortex Attenuation Method

    D. R. Croom | NTIS | 1976