Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter Page: 4 of 34
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NACA MR No. ESL17
S .. win 'are, 585 square feet
Vi velocity bf air entering nacelles, feet per second
VO free-stream veleoity, feet per second
VIjo. naoelle-inlet velocity ratio
- -total-pressure coefficient
Qb/Vo air-flow coefficient
a angle of attack of thrust axis relative to free-stream flow
absolute viscosity, pound-second per square foot
p mass density of air, slugs per cubic foot
C OFICURATIONS AND INS ITUINTATION
The YP-59A fighter airplane is powered by two Jet-propulsion
engines, each having a rating at sea level of 1650 pounds static
thrust at an engine speed of 16,500 rpm and an air consumption
of 34 pounds per second. The installation of the full-scale
test airplane in the altitude wind tunnel is shown in figure 1
with the tail surfaces removed and the engine nacelles faired.
Tests were conducted using the original configuration and a
revised configuration, which includes: (1) a revised boundary-
layer removal duct, (2) redesigned nacelle inlets, and (3) revised
engine cooling-air seals.
Boundary-Layer Removal Duct
Preliminary tests indicated that the original boundary-layer
removal duct (fig. 2 (a)) did not remove a sufficient quantity of
the low energy air in the boundary layer because of high energy
losses caused by approximately 2700 of bends and flow restrictions
in the duct. The revised boundary-layer removal duct (fig. 2 (b))
extends directly back from the inlet following the lower contour
of the nacelle and discharges behind the engine baffle.
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Preston, G. Merritt; Black, Fred O., Jr. & Jagger, James M. Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter, report, February 1946; (digital.library.unt.edu/ark:/67531/metadc61183/m1/4/: accessed February 25, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.