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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-Tunnel Investigation of Paraglider Models at Supersonic Speeds


    Contributors:

    Publication date :

    1961


    Size :

    18 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English