Effect of yaw and angle of attack on pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet at a Mach number of 2.71 Page: 2 of 21
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
TECH LIBRARY KAFB, NM
NACA RM LkG22 JJMIIJIIEIII UI
0144092
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
EFFECT OF YAW AND ANGLE OF ATTACK ON PRESSURE RECOVERY
AND MASS-FLOW CHARACTERISTICS OF A RECTANGULAR
SUPERSONIC SCOOP INLET AT A MACH
NUMBER OF 2.71
By Raymond J. Comenzo and Ernest A. Mackley
SUMMARY
An investigation has been conducted'of the effect of yaw and angle
of attack on the total-pressure recovery and mass-flow characteristics
of a rectangular supersonic scoop inlet designed to have low external
drag at a Mach number of 2.7 and an angle of attack of 00. Total-
pressure recovery and mass-flow data are presented for a Mach number
of 2.71 at angles of yaw of 00, 2.50, and 50 and angles of attack of
00 and 50. Total-pressure recovery, static pressure, and Mach number
distributions at the subsonic diffuser exit are presented.
An increase in angle of yaw caused small decreases in maximum
total-pressure0recovery at both angles of at ack tes ed. At an angle
of attack of 0 and angles of yaw of 0 , 2.5, and 5 , the maximum
total-pressure recoveries'obtained were 0.76, 0.71, and 0.68, respec-
tively. The mass-flow ratio of the inlet for both angles of attack
at maximum total-pressure recovery increased for a yaw angle of 205
and then decreased slightly upon increasing the angle of yaw to 5
The total-pressure and static-pressure distributions at maximum average
total-pressure recovery were generally uniform for all angles of yaw
and attack. The small variations in total pressure which did exist,
however, caused fairly large variations in local Mach number at the
rake station.
INTRODUCTION
A rectangular supersonic scoop inlet designed for low drag at an
angle of attack of 00 and a Mach number of 2.7 and reported in- - - -- - -- -. - ---- - ,- - ...-_ - -- - --- -- r C - - -.. -.-_ .... . _ ----__ -.-T I .-.- _--) -- --r .._ - - ._ _._ _-
Upcoming Pages
Here’s what’s next.
Search Inside
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.
Comenzo, Raymond J. & Mackley, Ernest A. Effect of yaw and angle of attack on pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet at a Mach number of 2.71, report, September 14, 1954; (https://digital.library.unt.edu/ark:/67531/metadc60807/m1/2/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.