A wind tunnel investigation was conducted in the Langley 30- by 60-Foot Tunnel to assess the free-flight test technique as a tool in research on wake vortex encounters. A typical 17.5-percent scale business-class jet airplane model was flown behind a stationary wing mounted in the forward portion of the wind tunnel test section. The span ratio (model span-generating wingspan) was 0.75. The wing angle of attack could be adjusted to produce a vortex of desired strength. The test airplane model was successfully flown in the vortex and through the vortex for a range of vortex strengths. Data obtained included the model airplane body axis accelerations, angular rates, attitudes, and control positions as a function of vortex strength and relative position. Pilot comments and video records were also recorded during the vortex encounters.


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    Titel :

    Application of Wind Tunnel Free-Flight Technique for Wake Vortex Encounters


    Beteiligte:
    J. M. Brandon (Autor:in) / F. L. Jordan (Autor:in) / R. A. Stuever (Autor:in) / C. W. Buttrill (Autor:in)

    Erscheinungsdatum :

    1997


    Format / Umfang :

    74 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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