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National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Investigation of an NACA 65-210 Semispan Wing Equipped with Circular Plug Ailerons and a Full Span Slotted  Flap

A wind-tunnel investigation.was made of the lateral-control charac-
teristics of a thin, low-drag, semispan wing equipped with three configura-
tions of circular plug ailerons and a full-span, 25-percent-chord, slotted
flap. The plug ailerons were located at the 68-percent-chord station,
spanned h9-2 percent of the semispan wing, and were constructed in five -
equal spanwise segments. The investigation was performed through a Mach
number range from 0.13 to 0-61. The Mach and Reynolds numbers were varied
simultaneously during the investigation-

The results of the investigation indicated that a satisfactory plug-
ailerdn configuration (a double~walled circular-plug-aileron configuration)
has been developed for use on high-speed unswept‘wing airplanes in conjunc-
tion with a full-span slotted flap. This plug-aileron configuration produced
increases in aileron effectiveness with increase in the Mach and.Reynolds
numbers, produced a fairly linear variation of rolling moment with aileron
projection, and produced appreciably larger rolling moments with the flap
deflected than with the flap retracted. In addition, this plug-aileron
configuration generally produced favorable yawing moments and also produced'
hinge moments which were of moderate value, had a stable variation over the
projection range, and exhibited either small or inconsistent changes with
increases in the Mach and Reynolds numbers.

As a solution to the high-lift and lateral-control problems presented
at take-off and landing by the high-performance airplanes currently in use ‘
or in the design stage, the National Advisory Committee for Aeronautics
has been investigating the characteristics of spoiler-type lateral-control
devices to be used in conjunction with full-span flaps-

The results of several relatively low-speed investigations made on
wings having conventional airfoil sections (references 1 to 8) indicated
some of the merits of spoiler-type lateral-control devices, such as control
at high angles of attack, favorable yawing moments, higher reversal speeds
than conventional ailerons because of the lower twisting moments of spoiler-
type devices, small stick forces, and theificreased effectiveness of
spoiler-type controls when fqu- span flaps are deflected. In addition,
these investigations indicated the increased effectiveness obtainable with
the plug- type spoiler- slot aileron (known as the "plug aileron ) as compared
with the effectiveness of the retractable aileron and also indicated the
large increase in wing lift obtainable through use of a full-span flap and
the generale superior characteristics obtainable with a slotted flap.