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• April 26, 2017 Create Date
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National Advisory Committee for Aeronautics, Research Memorandum - An Investigation at Low Speed of a 51.3° Sweptback Semispan Wing Equipped with 16.7% Chord Plain Flaps and Ailerons Having Various Spans and Three Trailing Edge Angles

A wind—tunnel investigation was performed at low speed to determine
the aerodynamic characteristics of a. 51.3° sweptback semispan wing
equipped with 16.7-percent—chord plain‘ flaps and ailerons having various
spans and. spanwise locations, and. with one span of aileron having trailing—
edge angles of 6°, 11:9, and 25°. Lift, drag, pitching—moment, and flap
hinge-moment data were obtained for the wing equipped with several spans of
sealed and unsealed flaps deflected up to 60°, and rolling—moment, yawing—
moment, hinge—moment, and aileron—seal—pressure data were obtained for the
various combinations of aileron span and. trailing—edge angles. In addition,
the wing aerodynamic characteristics were determined for a spoiler—type
aileron configuration having a span of 60 percent of the wing semispan and.
a projection of 5—percent wing chord. in conjunction with a. 92.5-percent—
span flap deflected 0°, 30°, and 60°.

The results indicate, in general, that changes in the wing angle of
attack, flap deflection, flap span, or flap spanwise location produced
trends in the wing lift, drag, pitching-ament, and. flap hinge—moment
characteristics that were similar to, but of different magnitude from,
the trends produced on unswept wings, except possibly at large angles of
attack near the wing stall. Also, changes inthe wing angle of attack,
aileron deflection, aileron span, or aileron spanwise location generally
produced effects on the swept—wing lateral—control characteristics that
were similar in trend to, but differing in magnitude from, the corresponding
effects produced on unswept wings. Notably, the data indicated that a.
given percent—span aileron would. ‘be most effective in producing roll when
it spans the center portion of the wing semispan.

At values of wing angle of attack below approximately llI-o, the rolling
moment produced by the spoiler—aileron configuration generally increased
with increase in the angle of attack, and. the yawing moment was favorable;
also, in this angle—of—attack range, the spoiler aileron generally produced
larger rolling moments with flap deflected than with flap undeflected.