An investigation was made in the Langley Unitary Plan wind tunnel to determine the behavior of paraglider models at moderate to high supersonic speeds. The models were deployed from a sting in the supersonic stream and steady-state aerodynamic performance data were obtained. Maximum values of the lift-drag ratio were about 1.4 at a Mach number of 2.65 and about 1.2 at a Mach number of 4.65. The angles of attack over which the models could be flown were limited by unsteady behavior of the canopy.


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    Titel :

    Wind-Tunnel Investigation of Paraglider Models at Supersonic Speeds


    Beteiligte:
    R. T. Taylor (Autor:in)

    Erscheinungsdatum :

    1961


    Format / Umfang :

    18 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch