Mach number, flow angle, and loss measurements downstream of a transonic fan-blade cascade
Loading...
Authors
Austin, Jeffrey G.
Subjects
NA
Advisors
Shreeve, Raymond P.
Date of Issue
1994-03
Date
March, 1994
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
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.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
NA
Identifiers
NPS Report Number
Sponsors
Funding
NA
Format
72 p.;28 cm.
Citation
Distribution Statement
Rights
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.