Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 4: stage and blade-row performance of stage with axial-discharge stators Page: 4 of 53
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NACA RM E540C26
cv specific heat of air at constant volume, Btu/(lb)(R)
D diffusion factor
g acceleration due to gravity, 32.17 ft/sec2
H total enthalpy, pgJT, sq ft/sec2
i incidence angle, angle between inlet-relative-air-velocity vector
and direction of tangent to blade mean line at leading edge, deg
8
J mechanical equivalent of heat, 778 ft-lb/Btu
K wall boundary-layer blockage factor
M absolute Mach number
HM' relative Mach number
P absolute total pressure, lb/sq ft
P' relative total pressure, lb/sq ft
p static pressure, lb/sq ft
r radius measured from axis of rotation, in.
T absolute total temperature, OR
t static temperature, OR
U blade speed, ft/sec
V absolute velocity of air, ft/sec
V' velocity of air relative to blade row, ft/sec
W weight flow of air, lb/sec
0 absolute air-flow angle measured from axis of rotation, deg
0' air-flow angle relative to blade row measured from axis of rota-
tion, deg
r ratio of specific heats for air, cp/cv, 1.3947
yo direction of tangent to blade mean camber line at leading or trail-
ing edge, deg
A symbol used to indicate change in quantity3
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Sandercock, Donald M.; Lieblein, Seymour & Schwenk, Francis C. Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 4: stage and blade-row performance of stage with axial-discharge stators, report, June 28, 1954; (https://digital.library.unt.edu/ark:/67531/metadc60722/m1/4/: accessed March 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.