A Preliminary Investigation of the Pressure Recovery of Several Two-Dimensional Supersonic Inlets at Mach Number of 2.01 Page: 3 of 30
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TECH LIBRARY KAFB, NM
NACA RM L54D14 (fy , 3 4 4 p
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
A PRELIMINARY INVESTIGATION OF THE PRESSURE RECOVERY OF
SEVERAL TWO-DIMENSIONAL SUPERSONIC INLETS
AT A MACH NUMBER OF 2.01
By Raymond J. Comenzo
A preliminary investigation of several two-dimensional supersonic
inlet configurations has been conducted at the Langley Aeronautical
Laboratory at a Mach number of 2.01 and an angle of attack of 00. Two
inlets similar in supersonic diffuser design but one having a subsonic
diffuser approximately equal to one-half the length of the other were
also investigated. Variable geometry was incorporated in the design
in an attempt to obtain high values of total-pressure recovery.
Maximum values of total-pressure recovery of 0.88 and 0.83 were
obtained for inlets designed for Mach numbers of 2.0 and 2.5, respec-
tively. A 50-percent decrease in subsonic diffuser length decreased
the maximum pressure recovery approximately 10 percent. Shadowgraphs
indicated extensive boundary-layer separation for the case of maximum
Various types of supersonic inlets have been investigated at and
below a Mach number of 2.0 to determine the relative advantages of
decelerating the free-stream air by means of a normal shock wave alone
(ref. 1) or by means of a conical or two-dimensional oblique shock wave
in conjunction with a normal shock wave (refs. 2 to 4). This report
presents the pressure-recovery results obtained from a preliminary
investigation of several two-dimensional supersonic inlets which utilized
a combination of oblique and normal shock waves to decelerate the flow.
The inlets tested appeared promising from theoretical calculations. In
addition, a method of obtaining a short-length subsonic diffuser was also
investigated. The two-dimensional inlet design consists of two wedges
staggered with respect to each other and is shown in figure 1. In order
to obtain high values of pressure recovery, variable geometry is
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Comenzo, Raymond J. A Preliminary Investigation of the Pressure Recovery of Several Two-Dimensional Supersonic Inlets at Mach Number of 2.01, report, June 23, 1954; (digital.library.unt.edu/ark:/67531/metadc60464/m1/3/: accessed January 18, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.