Transonic Investigation of an Axial-Flow Compressor Rotor With a Hub-Tip Ratio of 0.75 and Blades Having NACA A(Sub 2)I(Sub 8b) Mean Lines Page: 4 of 41
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NACA RM L57H08
W
d TwHaMmmnlil
gas weight flow, lb/sec
equivalent weight flow, corrected to sea-level conditions,
lb/sec
angle of attack, angle between flow direction and blade chord,
deg
gas flow angle, based on flow direction with respect to axial
direction, deg
ratio of specific heats
increase between stations 1 and 2
ratio of inlet stagnation pressure at test conditions to
11
NACA standard sea-level pressure, 2,116
efficiency based on momentum considerations
ratio of inlet stagnation temperature at test conditions to
NACA standard sea-level total temperature, 518.6
518.67
8QM
rotor turning, PjR - 2R, deg
gas density, slug/cu ft
solidity
total-pressure-loss coefficient,PR - P2R
PiR - PlSubscripts:
d design
h hub
R relative to rotor blade
t tip
z axial
8 tangentialp
0)
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Bernot, Peter T. & Savage, Melvyn. Transonic Investigation of an Axial-Flow Compressor Rotor With a Hub-Tip Ratio of 0.75 and Blades Having NACA A(Sub 2)I(Sub 8b) Mean Lines, report, September 30, 1957; (https://digital.library.unt.edu/ark:/67531/metadc64209/m1/4/: accessed March 28, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.