Preliminary flight measurements of the total-pressure recovery of a split-wing ram-jet inlet at Mach numbers from 1.4 to 3.16 Page: 3 of 30
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NACA RM SL54C05
The purpose of the investigation was to determine the total-
pressure recovery and internal flow characteristics of the design at
00 and -3 angle of attack, operating with a fixed area exit which gave
a diffuser-exit Mach number of approximately 0.19, over a range of
supersonic Mach number and Reynolds number.
Data are presented for both accelerating and decelerating flight
over a Mach number range from 1.40 to 3.16 and a Reynolds number range
from 5 x 106 to 17 x 106 based upon the unit "foot."
Acowl inlet capture area defined by inlet lips, sq ft
Acr choking area, sq ft
Ae entrance area to inlet defined along imaginary surface,
perpendicular to wedge surface from leading edge of inlet
lip, sq ft
Amin minimum area at inlet throat, sq ft
H total pressure, lb/sq ft
m measured mass flow through duct, slugs/sec
mO mass flow through a stream tube of area equal to inlet
capture area under free-stream conditions, slugs/sec
M Mach number
p static pressure, lb/sq ft
R gas constant, 55.5 3 ft/R
S static orifice
T static temperature, OR
V velocity, ft/sec
p density, slugs/cu ft
x local distance, in.
X total distance across station 6, in.
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Hinners, Arthur H., Jr. Preliminary flight measurements of the total-pressure recovery of a split-wing ram-jet inlet at Mach numbers from 1.4 to 3.16, report, March 4, 1954; (digital.library.unt.edu/ark:/67531/metadc60290/m1/3/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.