Investigation of a three-stage transonic research axial-flow compressor: aerodynamic design and overall performance Page: 4 of 59
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NACA RM L55G27 3 5
solidities are considerably lower; (2) the blade shapes are quite dif-
ferent; (3) all blade selections are based on low-speed cascade data;
and (4) the average design stage pressure ratio is about the same as
that of reference 5 though accomplished at a higher tip speed and is
greater than that of reference 6.
This report presents the design procedure, velocity diagrams, and
blading. The overall performance obtained for speeds ranging from 40
to l00 percent of design in Freon is presented. An analysis of the
effects of using either Freon or air as the test medium for flow through
compressor blade rows is also presented.
A flow area, sq ft
c blade chord, ft
Cp specific heat at constant pressure, ft Ib/lb/oF
D D-facor 1 e T where velocities are relative to
the blade element under consideration
K boundary-layer blockage factor
M Mach number
N corrected rotational speed (the ratio of actual rotational
speed to V8 ), rpm
n polytropic exponent
P stagnation pressure, b/sq ft
p static pressure, Ib/sq ft
Ap static pressure rise across a blade row, Pe - pi, ib/sq ft
qi inlet dynamic pressure, 4 piMi2, lb/sq ft
r radius, ft
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Savage, Melvyn & Beatty, Loren A. Investigation of a three-stage transonic research axial-flow compressor: aerodynamic design and overall performance, report, October 27, 1955; (digital.library.unt.edu/ark:/67531/metadc61670/m1/4/: accessed November 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.