A number of high aspect ratio supercritical wings in combination with a representative wide body type fuselage were tested in the Langley 8 foot transonic pressure tunnel. The wing parameters investigated include aspect ratio, sweep, thickness to chord ratio, and camber. Subsequent to these initial series of tests, a particular wing configuration was selected for further study and development. Tests on the selected wing involved the incorporation of a larger inboard trailing edge extension, an inboard leading edge extension, and flow through nacelles. Range factors for the various supercritical wing configurations are compared with those for a reference wide body transport configuration.


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    Title :

    The NASA supercritical-wing technology


    Contributors:

    Conference:

    CTOL Transport Technol. Conf. ; 1978 ; Hampton, VA, United States


    Publication date :

    1978-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :