Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets Page: 3 of 15
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2 . E NACA RM E52J10
The corners at the cowl and the inlet-splitter plate junctions
become more severe when the floor of a conical-type side inlet is designed
to follow the surface of a circular fuselage. Therefore, the effects of
fillets on the performance of a side inlet having sharp corners were
determined in the NACA Lewis 8- by 6-foot supersonic tunnel through a
range of free-stream Mach numbers and boundary-layer scoop heights.
Twin-scoop conical-type side inlets, with and without internal
corner fillets, mounted at the station of maximum diameter of the H
RM-10 body (reference 1) were investigated at zero angle of attack and
free-stream Mach numbers from 1.49 to 1.97. The Reynolds number, based
on model length ahead of the inlets, was approximately 17x106.
h height of wedge spacer for boundary-layer removal
M Mach number
m mass flow
P total pressure -
p static pressure
x distance from cowl lip, in.
8 boundary-layer thickness
c projected capture area of inlet
0 free stream
2 diffuser discharge station (17.5)
APPARATUS AND PROCEDURE
A photograph and a schematic diagram of the model, showing the twin
scoop inlets mounted diametrically opposite, are presented in fig-
ures 1 and 2(a), respectively. Details of the inlets are presented
in figure 2(b)
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Valerino, Alfred S. Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets, report, December 8, 1952; (https://digital.library.unt.edu/ark:/67531/metadc64540/m1/3/: accessed March 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.