A 60-degree delta wing, an F-106B, and an XB-70 model with and without flap deflections were tested in static and dynamic ground effect in the 36-by-51-inch subsonic wind tunnel at the University of Kansas. Dynamic ground effect was measured with movable sting support. For flow visualization, a tufted wire grid was mounted on the movable sting behind the model. Test results showed that lift and drag increments in dynamic ground effect were always lower than static values. Effect of the trailing edge flap deflections on lift increments was slight. The fuselage reduced the lift increments at a given ground height. From flow visualization under static conditions, the vortex core was seen to enlarge as the ground was approached.


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    Titel :

    Experimental investigation of dynamic ground effect


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.06.1989



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Experimental investigation of dynamic ground effect

    LEE, PAI-HUNG / LAN, C. EDWARD / MUIRHEAD, VINCENT U. | AIAA | 1989


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    Investigation of dynamic ground effect

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    Experimental and Analytic Investigation of Ground Effect

    Traub, Lance W | Online Contents | 2015