Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control Page: 3 of 41
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NACA RM E52G23
Inlet total-pressure recovery decreased markedly with reduced boundary-
layer-scoop mass flow. Inlet stability was sensitive to subcritical scoop
operation, particularly at the larger scoop heights investigated for the
turbulent boundary layer and for all scoop heights investigated for the
laminar boundary layer.
INTRODUCTION
The side inlet must operate in the presence of the flow field and
boundary layer over the surface on which it is installed. Research con- H
ducted in the Mach number range from about 1.5 to 2,0 has Indicated that
side-inlet performance can be made comparable to nose-inlet performance
by suitable control of the initial'boundary layer. Boundary-layer
removal has been employed successfully in this respect (references 1
to 4).
This investigation was conducted at the NACA Lewis laboratory to
extend the study of side-inlet performance with various amounts of
boundary-layer removal to a free-stream Mach number of about 3.0. The
side inlet consisted of half of a single-shock conical-spike supersonic
inlet mounted on a flat plate and alined at zero angle of attack and
yaw with respect to the local free stream. Boundary-layer removal was
accomplished with a variable-height ram-type scoop with a straight lead-
ing edge positioned. at the spike tip.
The initial boundary layer at the inlet ras varied by changing the
plate length upstream of the inlet. Transition to turbulent flow was
forced on the longest plate by roughness added near the plate leading
edge. Both the inlet and the boundary-layer scoop were operated over
a range of mass-flow ratios at various scoop heights in both laminar
and turbulent boundary layers.
SYMBOLS
The following symbols are used in this report:
A area
h height of boundary-layer-removal scoop above flat plate
h/5 dimensionless boundary-layer-scoop-height parameter
L plate length, measured frcm leading edge to spike tip
L/R dimensionless plate-length parameterm mass flow
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Piercy, Thomas G. & Johnson, Harry W. Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control, report, September 10, 1952; (https://digital.library.unt.edu/ark:/67531/metadc59332/m1/3/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.