Detailed flow surveys downstream of the corner turning vanes and downstream of the fan inlet guide vanes have been obtained in a 0.1-scale model of the NASA Lewis Research Center's proposed Altitude Wind Tunnel. Two turning vane designs were evaluated in both corners 1 and 2 (the corners between the test section and the drive fan). Vane A was a controlled-diffusion airfoil and vane B was a circular-arc airfoil. At given flows the turning vane wakes were surveyed to determine the vane pressure losses. For both corners the vane A turning vane configuration gave lower losses than the vane B configuration in the regions where the flow regime should be representative of two-dimensional flow. For both vane sets the vane loss coefficient increased rapidly near the walls.


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    Title :

    Detailed Flow Surveys of Turning Vanes Designed for a 0.1-Scale Model of NASA (National Aeronautics and Space Administration) Lewis Research Center's Proposed Altitude Wind Tunnel


    Contributors:
    R. D. Moore (author) / R. J. Shyne (author) / D. R. Boldman (author) / T. F. Gelder (author)

    Publication date :

    1987


    Size :

    151 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English