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• December 4, 2016 Create Date
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National Advisory Committee for Aeronautics, Technical Notes - High Speed Wind Tunnel Investigation of an NACA 65-210 Semispan Wing Equipped with Plug and Retractable Ailerons and a Full Span Slotted Flap

A high-speed wind-tunnel investigation was made to determine the
lateral-control characteristics of plug and retractable ailerons on a
thin, low-drag, semispan wing equipped with a 251percent—chord, full-span,
slotted flap. The ailerons investigated covered #9 percent of the wing
semispan, were located at the 70-percent-chord station, and were perfo~
rated and segmented. The investigation was performed through a Mach
number range from 0.13 to 0.71. The Mach and Reynolds numbers were
simultaneously varied during the investigation.

With flap retracted or deflected, the values of rollingamoment
coefficient produced by projection of the basic plug or retractable
ailerons generally increased with increase in the Mach and Reynolds
numbers, particularly for small projections in the flap—retracted config-
uration. The rolling effectiveness of the basic plug aileron generally
increased with increase in the angle of attack in both flap configu-
rations; whereas the rolling effectiveness of the basic retractable
aileron generally increased with increase in the angle of attack only
at small projections in the flap-retracted configuration. Almost linear
control effectiveness with aileron projection probably would be provided
by both ailerons at all speeds in the flap-retracted configuration.
Appreciably larger values of rollingfimoment coefficient were produced
at all projections of the basic plug and retractable ailerons with the
full-span flap deflected than were produced with flap retracted, and
large values of rolling—moment coefficient Were produced by both ailerons
above the flap-deflected stall angle. Inconsistent trends of reversed
rolling effectiveness for small projections were exhibited by the
retractable aileron with flap deflected.

Favorable values of yawingimoment coefficient that became more
favorable with aileron projection, less favorable with increase in the
angle of attack, and were essentially unaffected by increase in the
Mach number were generally Obtained with the basic plug and retractable
ailerons below the wing stall angle.