Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular-Wing and Body Combinations at a Mach Number of 1.94 Page: 3 of 53
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:
2 CGe NACA RM L55114-
experimentally at subsonic, transonic, and supersonic speeds. A com-
pilation of much of the past work relating to these problems can be
found in reference i. Since the publication of reference 1, additional
work has been done, some of which is presented in reference 2. In this
reference, an experimental investigation was made at a Mach number
of 1.62 to determine the interference aerodynamic characteristics of a
series of triangular-wing and body combinations.
The present report can be considered an extension of reference 2
to include interference data of the same series of triangular-wing and
body combinations but at a Mach number of 1.94. Similar to reference 2,
the results presented herein place emphasis upon lift and pitching-
moment interference, with drag interference results included. Compari-
sons of the measured interference quantities are made with theory. The
investigation involved a series of flat-plate triangular wings of varying
size having beveled leading and trailing edges in combination with a
body of revolution having a fineness ratio of 10.27. Some additional
tests were also made involving two of the triangular wings and a body
having a fineness ratio of 9.15. Reynolds numbers of the tests varied
from 0.25 x 106 to 2.46 x 106 based on the wing mean aerodynamic chord.
Four of the wings had semiapex angles of 30 with an exposed aspect
ratio of 2.3, whereas the remaining three wings had semiapex angles of
450 with an exposed aspect ratio of 4.
a angle of attack of body
b total wing span
cr wing root chord
mean aerodynamic chord of exposed wing
CL lift coefficient, Lift/qS
CD drag coefficient, Drag/qS
Cm pitching-moment coefficient about 50 percent mean aero-
dynamic chord, Moment/qSE
CX . longitudinal-force coefficient for exposed wing in pres-
ence of body, X/qS
1 - rc
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.
Coletti, Donald E. Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular-Wing and Body Combinations at a Mach Number of 1.94, report, December 21, 1955; (digital.library.unt.edu/ark:/67531/metadc61653/m1/3/: accessed January 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.