Under a pair of Space Act Agreements between NASA and Honeywell Aerospace, a model-scale (22 in.-diameter fan) acoustic wind tunnel test was carried out in the fall of 2014 in the NASA Glenn Research Center 9- by 15-Foot Low-Speed Wind Tunnel. The goal was to obtain acoustic pressure measurements for far-field, inlet and exit rotating rake, and in-duct microphone locations. This supersonic-tip-speed fan was tested in three bypass duct configurations: hard-wall, traditional liner, and advanced multiple-degree-of-freedom. Limited aerodynamic data was collected to verify the expected operating conditions. Preliminary analysis of the acoustic data finds it suitable for use in evaluating current NASA and Honeywell Aerospace acoustic tools and liner design practices. This report provides an overview of the test and some preliminary findings.


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    Title :

    Acoustic Testing of a High-Tip-Speed Fan with Bypass-Duct Liners - Overview


    Contributors:

    Publication date :

    2019


    Size :

    46 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Acoustic Testing of a High-Tip-Speed Fan with Bypass-Duct Liners - Overview

    Miller, Christopher J. / Stephens, David B. / Sutliff, Daniel L. | NTRS | 2019


    Acoustic Testing of a High-Tip-Speed Fan with Bypass-Duct Liners

    Christopher J Miller / David B Stephens / Daniel L Sutliff | NTRS | 2018