Data are presented on velocity measurements made with hot wire anemometers in the wake of a model of the CV-990 aircraft and a rectangular wing in the NASA-Ames 2.14x3.05 meter (7- by 10-foot) wind tunnels. Variables included angle of attack, tunnel speed and axial distance up to 12 chord lengths downstream from the wing trailing edge. Effects of deflecting trailing edge flaps and small spoiler panels are shown. (Author)


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    Title :

    Wind Tunnel Test Data for Wing Trailing Vortex Flow Survey


    Contributors:

    Publication date :

    1972


    Size :

    94 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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