Investigations of the damping in roll of swept and tapered wings at supersonic speeds Page: 3 of 36

2 NACA RM 153A13
The linear theory of supersonic flow has provided damping-in-roll
predictions for a large class of wing plan forms (see refs. 1 to 5).
However, the experimental information presently available on the rolling
characteristics of wings at supersonic speeds is rather limited. The
damping in roll of a group of rectangular and triangular wings at super-
sonic speeds was investigated in the langley 9-inch supersonic tunnel
(ref. 6). Free-flight investigations utilizing rocket-propelled test
vehicles have been made of the damping in.roll of several wings, including
a triangular-wing configuration geometrically similar .to one of those used
in reference 6 (see ref. 7). Numerous other free-flight tests utilizing
rocket-propelled vehicles have been made of the rolling characteristics
of various wing-body and wing-body-tail combinations, including those
reported in references 8, 9, and 10.
The purpose of the present investigation was to supply experimental
values of CZ for a series of 33 swept and tapered wings and to comn-
pare them with theoretical predictions. For 31 of the wings the leading-
and trailing-edge sweep angles and taper ratios were varied systematically,
and the thickness was held constant. Also two thinner wings were con-
structed to study thickness effects on CZ . The plan forms selected
p _
gave data through the leading-edge-sweep-angle range such that the
leading edge passed from behind to ahead of the Mach cone emanating from
the wing apexes. The taper ratios were 0 and 0.25.
All wings were mounted on a small cylindrical sting and were tested
at Mach numbers of 1.62, 1.93, and 2.41. The Reynolds number range of
the tests was from 0.52 x 106 to 2.37 x 106, based on the wing mean
aerodynamic chord."
b w i n g s p a n.... . . ..
S total wing area
A aspect ratio, b2/S
cr wing root chord (calculated from measured wing dimensions)
ct wing tip chord
K wing taper ratio, ct/cr
A angle of sweep of wing leading edge, positive for sweepback
-4. .

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McDearmon, Russell W. & Heinke, Harry S., Jr. Investigations of the damping in roll of swept and tapered wings at supersonic speeds, report, March 3, 1953; ( accessed May 20, 2019), University of North Texas Libraries, Digital Library,; crediting UNT Libraries Government Documents Department.

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