Determination of boundary layer transition and separation on double arc compressor blades in a large subsonic cascade.
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Authors
McGuire, Alan G.
Subjects
cascade
DCA blading
flow visualization
DCA blading
flow visualization
Advisors
Shreeve, Raymond P.
Date of Issue
1983-09
Date
September 1983
Publisher
Language
en_US
Abstract
The china clay technique for flow visualization was used
to determine the surface flow on a double circular arc (DCA)
compressor blade in a large rectilinear subsonic cascade wind
tunnel. A calibration experiment using a large flat plate
model is also reported which allowed the drying patterns on
the DCA blading to be interpreted. Natural transition
occurred on the flat plate at a Reynolds Number based on
transition location of 0.8 x 10⁶, and on the suction surface
of the DCA blading at significant negative incidence angles
at a Reynolds Number based on transition location of approximately
0.5 x 10⁶. At incidence angles larger than -3⁰ , the
DCA blade showed a leading edge separation bubble with
turbulent reattachment.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
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.