Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets Page: 4 of 15
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NACA RM E52Jl0
The inlets were designed so that the oblique shocks generated by
a the 250 half-cone centerbodies would fall slightly ahead of the cowl
lips for the local Mach number ahead of the inlets of 2.06 which occurs
at a free-stream Mach number of 2.0. The local Mach number was deter-
mined from a preliminary survey of the flow conditions at station 45 of
the RM-10 body.
Two cross-sectional views of the inlets, with and without 1/4-inch
fillets, are shown in figure 2(b). The corner fillets were tapered from
H zero radius at the lip station to a 1/4-inch radius at station 1 and
remained constant to diffuser station 24.5. The cowling cross section
was gradually changed from a nearly sector-shaped lip of radius 1.33 inches
to a circular cross section of radius 1.41 inches at diffuser station 24.5.
The area variations of the inlets without and with corner fillets (fig. 3)
were made identical by slightly reducing the size of the centerbody.
Typical cross sections of the inlets, showing the cowling transition from
the lip to the circular cross section at the rear of the inlet, are also
included in figure 3.
Boundary-layer removal was accomplished by means of wedge-shaped
spacers placed between the inlets and the RM-10 body, which bypassed the
boundary-layer air around the inlets. From the preliminary flow survey
at station 45 of the EM-10 body, the boundary-layer thickness was
determined to be approximately 3/8 inch at zero angle of attack. Spacers
of 3/8-inch and 3/4-inch heights, which were alined with the tips of the
sweptback splitter plates of the inlets (see figs. 1 and 2(a)) were
employed to obtain the boundary-layer removal parameters h/ of 1.0
and 2.0, respectively, at zero angle of attack. The condition of
h/8 = 0 kas obtained by placing the inlets directly on the RM-lO body.
With the h/ = 0 configuration, spacers were used at the rear of the
RM-lO body for alinement purposes..
All the pressure instrumentation was located at inlet station 17.5
and consisted of 18 total-pressure tubes and 4 wall static orifices for
one inlet and 4 wall static orifices for the other inlet. The inlet
mass flows were varied by means of remotely controlled exit plugs and
were computed from the average measured total pressures at the choked
RESULTS AND DISCUSSION
The experimental results of the inlets with and without corner
fillets are presented in figures 4, 5, and 7 as the variation of the
total-pressure recovery with mass flow ratio m2/mc for the three
boundary-layer bypass wedges and a range of free-stream Mach number.
* The mass flow ratio m2/mc is defined as the ratio of the mass flow
passing through the inlet to the mass flow in a free-stream tube area
equal to the projected capture area of the inlet.
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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; (digital.library.unt.edu/ark:/67531/metadc64540/m1/4/: accessed February 23, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.