Comparison at supersonic speeds of translating spike inlets having blunt- and sharp-lip cowls Page: 4 of 41
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NACA RM E54J07 3
corrected air-flow parameter, b/sec/sq ft
W weight flow, lb/sec
x axial distance from cowl lip, in.
a angle of attack, deg
I ratio of specific heats for air, 1.4
total pressure divided by NACA standard sea-level static
9 stream total temperature divided by NACA standard sea-level
e, cowl-position parameter (angle between axis of diffuser and
line joining apex of cone to cowl lip), deg
P theoretical oblique shock angle, deg
o free stream
2 diffuser exit
3 air-flow measuring station
APPARATUS AND PROCEDURE
The inlet model was supported below the tunnel centerline by a strut-
supported sting (fig. 1(a)). Geometric details of the sharp-lip and
blunt-lip cowls are shown in figures 1(b) and (c), respectively. Co-
ordinates of both cowls are referenced to a common axial station (x = 0)
located upstream of the lip. All coordinates downstream of x = 2.688
are identical for both cowls. The blunt-lip cowl had a larger capture
area, hence less projected frontal area than the sharp-lip cowl.
Details of the centerbody are shown in figure 1(d). The portion of
the centerbody that translates was composed of a 500 included-angle
conical spike which faired into a cylindrical section. This cylindrical
section translated over a fixed cylindrical portion of the centerbody.
The diffuser-area variation of both inlets for various positions of the
spike is shown in figure 2.
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Gorton, Gerald C. & Dryer, Murray. Comparison at supersonic speeds of translating spike inlets having blunt- and sharp-lip cowls, report, January 19, 1954; (digital.library.unt.edu/ark:/67531/metadc64825/m1/4/: accessed April 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.