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

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Author
Austin, Jeffrey G.
Date
1994-03Advisor
Shreeve, Raymond P.
Second Reader
NA
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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.Collections
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