Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body Page: 4 of 34
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NACA I E52K18
In order to evaluate this type of inlet, an investigation was con-
ducted in the NACA Lewis 8- by 6-foot supersonic wind tunnel on an inlet
consisting of a hemispherical-nosed centerbody with a probe projected
upstream. Pressure-recovery, drag, and mass-flow characteristics are
presented for Mach numbers from 1.6 to 2.0 and angles Of attack to 9.
The Reynolds number, based on inlet diameter, was approximately
2.07X106. Data for a conical inlet installed on the same model (refer- o
ence 9) are included for comparison.
The following symbols are used in this report:
A area, sq ft
CD external-drag coefficient D/QoAm
D drag force, lb
L length of probe, in.
M Macoh number
m .mass flow, slugs/sec
m/m0 mass-flow ratio
P total pressure, lb/sq ft
p static pressure, lb/sq ft
q dynamic pressure, ypM2/2, Ib/sq ft
R radius of hemispherical nose, in.
o angle of attack, deg
r ratio of specific heats for air
0 free stream
2 station 1/2 inch upstream of honeycomb
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Hearth, Donald P. & Gorton, Gerald C. Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body, report, January 19, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59520/m1/4/: accessed April 22, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.