Preliminary flight measurements of the total-pressure recovery of a split-wing ram-jet inlet at Mach numbers from 1.4 to 3.16 Page: 3 of 30
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA RM SL54C05
The purpose of the investigation was to determine the total-
pressure recovery and internal flow characteristics of the design at
00 and -3 angle of attack, operating with a fixed area exit which gave
a diffuser-exit Mach number of approximately 0.19, over a range of
supersonic Mach number and Reynolds number.
Data are presented for both accelerating and decelerating flight
over a Mach number range from 1.40 to 3.16 and a Reynolds number range
from 5 x 106 to 17 x 106 based upon the unit "foot."
Acowl inlet capture area defined by inlet lips, sq ft
Acr choking area, sq ft
Ae entrance area to inlet defined along imaginary surface,
perpendicular to wedge surface from leading edge of inlet
lip, sq ft
Amin minimum area at inlet throat, sq ft
H total pressure, lb/sq ft
m measured mass flow through duct, slugs/sec
mO mass flow through a stream tube of area equal to inlet
capture area under free-stream conditions, slugs/sec
M Mach number
p static pressure, lb/sq ft
R gas constant, 55.5 3 ft/R
S static orifice
T static temperature, OR
V velocity, ft/sec
p density, slugs/cu ft
x local distance, in.
X total distance across station 6, in.
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Hinners, Arthur H , Jr. Preliminary flight measurements of the total-pressure recovery of a split-wing ram-jet inlet at Mach numbers from 1.4 to 3.16, report, March 4, 1954; (digital.library.unt.edu/ark:/67531/metadc60290/m1/3/: accessed January 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.