An investigation has been conducted in the NASA Langley Research Center's 30- by 60-Foot Wind Tunnel on a full-scale semispan model to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing utilizing the HSNLF(1)-0213 airfoil section and a single slotted flap system. In addition to the high-lift studies, evaluations of boundary layer transition effects, the effectiveness of a segmented leading-edge droop for improved stall/spin resistance, and roll control effectiveness with and without flap deflection were made. The wind-tunnel investigation showed that deployment of a single-slotted trailing-edge flap provided substantial increments in lift. Fixed transition studies indicated no adverse effects on lift and pitching-moment characteristics for either the cruise or landing configuration. Subscale roll damping tests also indicated that stall/spin resistance could be enhanced through the use of a properly designed leading-edge droop.


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    Titel :

    Full-scale semi-span tests of an advanced NLF business jet wing


    Beteiligte:

    Erscheinungsdatum :

    1987-10-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Full-Scale Semi-Span Tests of an Advanced NLF Business Jet Wing

    Muchmore, C. Byram / Hahne, David E. / Jordan, Frank L. et al. | SAE Technical Papers | 1987


    Full-scale wing tests

    Engineering Index Backfile | 1946