Two turning vane designs were experimentally evaluated for the fan-drive corner (corner 2) coupled to an upstream diffuser and the high-speed corner (corner 1) of the 0.1 scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. For corner 2 both a controlled-diffusion vane design (vane A4) and a circular-arc vane design (vane B) were studied. The corner 2 total pressure loss coefficient was about 0.12 with either vane design. This was about 25 percent less loss than when corner 2 was tested alone. Although the vane A4 design has the advantage of 20 percent fewer vanes than the vane B design, its vane shape is more complex. The effects of simulated inlet flow distortion on the overall losses for corner 1 or 2 were small.


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    Title :

    Experimental Evaluation of Turning Vane Designs for High-Speed and Coupled Fan-Drive Corners of 0.1-Scale Model of NASA Lewis Research Center's Proposed Altitude Wind Tunnel


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

    Publication date :

    1987


    Size :

    54 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English