High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser Page: 4 of 21
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NACA RM E58A09
M Mach number
0O 0.. 0 0
"g " @e
* 0 Se "5 0
* 5 5r "
05 ""9 55
0 55 @0 S 500
OS. " * oS
* 0" " 0 "
" " 0 0 0" 5
- S . " " " "
* 000 O0
S 00 5 O0
m3/m0 inlet mass-flow ratio, P3A3V3/POAianV
P total pressure, b/sq ft
P3/PO total-pressure recovery
p static pressure, b/sq ft
q dynamic pressure, b/sq ft
V air velocity, ft/sec
x distance, in.
Ca angle of attack, deg
9Z cowl-position parameter, angle between axis of symmetry and line
from spike tip to cowl lip, deg
p density of air, lb/cu ft
O conditions in free stream
3 conditions at diffuser exit
The inlet configuration studied herein utilized a cylindrical cowl
with all-external isentropic compression that was focussed at the lip
and limited by the requirements for shock attachment on the cowl. At
Mach 4.0, the theoretical Mach numbers behind the terminal shock are
only about 0.5. The corresponding dynamic head is relatively small. In
fact, by assuming a complete loss of this dynamic head, which might hap-
pen in the mixing processes involved in dumping the flow, little effect
on kinetic-energy efficiency would result. For example, at Mach 4.0 a
pressure recovery of 0.54, or a kinetic-energy efficiency of 0.95, might
be possible with no turning loss and an ideal subsonic diffuser; whereas
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Connors, J. F. & Flaherty, R. J. High mach number, low-cowl-drag, external- compression inlet with subsonic dump diffuser, report, May 12, 1958; (digital.library.unt.edu/ark:/67531/metadc52971/m1/4/: accessed September 19, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.