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National Advisory Committee for Aeronautics, Technical Notes - Pressure Distribution Over a Plug Type Spoiler Slot Aileron on a Tapered Wing with Full Span Slotted Flaps

A pressure-distribution investigation was made in the
Langley 7- by 10-foot tunnel of a plug-type spoiler—slot
aileron on a semispan tapered-wing model of a typical
fighter airplane equipped with full-span'slotted flaps.
The results of the investigation indicate peak pressures'
on a plug-typeISpoiler-slot aileron that may result in a
compressibility shock on the plug aileron at high speed.
The maximum loads on the plug aileron occurred in the
high-speed condition for maximum up aileron deflection.

A pressure-distribution investigation was made in the
Langley 7- by 10-foot tunnel of the plug-type spoiler-slot
aileron on a tapered-wing model of a typical fighter air—
plane with full-span slotted flaps. -A plug—type aileron
is essentially a tapered plug that fits in through a slot
in the wing to conform to the original external wing con-_
tour when in a neutral position. When the aileron is
deflected, the plug projects through the upper surface of
the Wing as a spoiler and, at the same time, makes a slot ~
through the wing behind the spoiler.

The purpose of this investigation was to obtain the.
air loads on the aileron designated as plug aileron 5 in
reference 1. Tests were made at various angles of attack
for both flap-retracted and flap-deflected conditions. '”_
In order'to obtain more complete data, pressures were -=
measured on a solid plug-type spoiler- slot aileron, desig—
nated as plug aileron 2 in reference 1, at“two angles of
attack with flap retracted.

In order to make the text and figures herein more
concise, the term “plug aileron“ is substituted for the
previously used term “plug-type spoiler-slot aileron" and
the term "plug" is used in the figures where reference is
made to the component parts of the plug aileron.

A semispan wing model was mounted in the Langley
7- by 10—foot tunnel (reference 2) as shown schematically
in figure 1. The wing model represents the cross—hatched
part of the airplane shown in figure 2. The root chord
of the model was adjacent to one of the vertical walls of
the tunnel, the vertical wall thereby serving as a reflec—
tion plane. The flow over a semispan model in this setup
is essentially the same as the flow would be over a com—
plete model in a 7— by 20~foot tunnel. Provision was made
for changing the angle of attack while the tunnel was in
operation.