Control Effectiveness Load and Hinge-Moment Characteristics of a Tip Control Surface on a Delta Wing at a Mach Number of 1.9 Page: 4 of 43
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NACA RM L9H05
is not unduly sensitive to flow separation near the wing trailing edge.
To learn more about such controls, an investigation has been conducted -
in the Langley 9- by 12-inch supersonic blowdown tunnel on a half-delta
control mounted at the tip of a delta wing for a Mach number of 1.9 and_...
a Reynolds number of 4 X 106. Similar investigations are being under-
taken by the free-flight rocket technique, and acknowledgement is made
of rocket test data contained herein supplied by the Langley Pilotless
Aircraft Research Division.
The wing-model leading edge was swept back 600, and the outer one-
third of the exposed span consisted of a tip control which rotated about
an axis normal to the root chord. In an attempt to minimize possible
gap effects caused by deflecting the control. surface, tests were made.
with a fence mounted at the outer end of the wing panel. Control sur-
faces of two thicknesses were tested. In some instances the results
have been compared with calculated characteristics.
COEFFICIENTS AND SYMBGLS
CL lift coefficient L
CD drag coefficient ()
C itching-moment coefficient (-)
CZ rolling-mament coefficient '
Cn yawing-moment coefficient sb
M' pitching moment about center of area of
L rolling mnent about axis of fuselage
N yawing moment about an axis perpendicular to
fuselage center line
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Conner, D. William & May, Ellery B., Jr. Control Effectiveness Load and Hinge-Moment Characteristics of a Tip Control Surface on a Delta Wing at a Mach Number of 1.9, report, October 7, 1949; (https://digital.library.unt.edu/ark:/67531/metadc58388/m1/4/: accessed May 24, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.