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Mach number, flow angle, and loss measurements downstream of a transonic fan-blade cascade

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Author
Austin, Jeffrey G.
Date
1994-03
Advisor
Shreeve, Raymond P.
Second Reader
NA
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Abstract
Two dimensional flow measurements of Mach number and flow angle were conducted downstream of a transonic fan-blade cascade at a mach number of 1.4 to provide baseline data for assessing the effect of vortex generating devices on the suction surface shock-boundary layer interaction. The experimental program consisted of the design and calibration of a traversing three-port pneumatic probe to measure Mach number and flow angle and initial cascade measurements to provide baseline data for the fully-mixed-out total pressure loss coefficient and flow turning angle. Similar tests are planned with the vortex generating devices installed. Comparisons with and without the vortex generating devices are needed to quantify the overall effect on the shock-boundary interaction in a transonic fan-blade passage, and to assess the potential for using vortex generating devices in military engine fans.
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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http://hdl.handle.net/10945/30868
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  • 1. Thesis and Dissertation Collection, all items

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Showing items related by title, author, creator and subject.

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    Model fan passage flow simulation 

    Myre, David D. (Monterey, California. Naval Postgraduate School, 1992-12);
    Two-dimensional experimental and numerical simulations of a transonic fan blade passage were conducted at a Mach number of 1.4 to provide baseline data for the study of the effects of vortex generating devices on the suction ...
  • Thumbnail

    The effects of low-profile vortex generators on flow in a transonic fan-blade cascade 

    Gamerdinger, Peter M. (Monterey, California. Naval Postgraduate School, 1995-03);
    Two dimensional fully-mixed-out flow conditions were measured downstream of a two-passage transonic fan-blade cascade which had low-profile vortex generators (VGs) attached to the suction surfaces of the blades. The ...
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    Static pressure measurements of the shock-boundary layer interaction in a simulated fan passage 

    Golden, William L. (Monterey, California. Naval Postgraduate School, 1992-03);
    Two-dimensional experimental and numerical simulations of a transonic fan blade passage (M = 1.4) were conducted to provide baseline data for the study of the effects of vortex generating devices on shock-boundary layer ...
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