Investigation at Mach numbers of 1.41, 1.61, and 1.82 of two variable-geometry inlets having two-dimensional compression surfaces Page: 4 of 56
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NACA RM L54KI4 3
h height of boundary-layer bleed, in.
M free-stream Mach number
m mass flow, slugs/sec
mo free-stream mass flow, slugs/sec
Pe duct-exit static pressure, lb/sq ft
Po free-stream static pressure, lb/sq ft
qo free-stream dynamic pressure, lb/sq ft
T engine thrust, lb
TI engine thrust at 100-percent pressure recovery, lb
Ve duct-exit velocity, ft/sec
Vo free-stream velocity, ft/sec
W weight of flow of air, lb/sec
y vertical distance in duct, in.
H/Ho total pressure recovery at compressor face
HL/H0 local total pressure recovery in diffuser
m/mo mass-flow ratio, based on inlet capture area of 0.0466 sq ft
for inlet A and 0.0511 sq ft for inlet B
angle of attack measured from inlet axis, deg
6 engine-inlet total pressure divided by NACA sea-level
pressure
e inlet total temperature divided by NACA sea-level temperature
angle of compression surface (measured from inlet axis on
inlet A), deg
'angle of yaw, deg
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Hasel, Lowell E. Investigation at Mach numbers of 1.41, 1.61, and 1.82 of two variable-geometry inlets having two-dimensional compression surfaces, report, February 23, 1956; (https://digital.library.unt.edu/ark:/67531/metadc60835/m1/4/: accessed April 18, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.