Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer Page: 4 of 20
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NACA RM E53L28b
_b P dy
P0 POa
Re
U5
U
V
X, Y, Y', Z
y
ca
6
Subscripts:
bZ
cr
max
0, 2, 3
1, 2, 3ratio of area-weighted average total pressure in
boundary layer to free-stream total pressure
Reynolds number, pOVOZ/O0 (Z = 47.83 in.)
local stream velocity outside boundary layer
velocity in boundary layer
velocity
duct coordinate dimensions (see figs. 3 and 4)
distance normal to fuselage model surface
angle of attack, deg
boundary-layer thickness (defined by u/U6 = 0.99),
inlet station bZ, in.
viscosity
densityplane of boundary-layer survey
critical
maximum
free-stream conditions
inlet stations (see fig. 2)APPARATUS AND PROCEDURE
Two inlets were alternately installed on the afterbody of a one-
tenth scale model of a typical supersonic airplane fuselage. A photo-
graph of the installation in the NACA Lewis 8- by 6-foot supersonic
tunnel, together with an enlarged view of the scoop inlet, is shown
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Pennington, Donald B. & Simon, Paul C. Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer, report, March 10, 1954; (https://digital.library.unt.edu/ark:/67531/metadc64496/m1/4/: accessed March 28, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.