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• December 2, 2016 Create Date
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Two Dimensional Wind Tunnel Investigation of Sealed 0.22 Chord Internally Balanced Ailerons of Different Contour on an NACA 65(112)-213 Airfoil

A two—dimensional wind—tunnel investigation_was made of __
two interchangeable sealed 0. 22- airfoil- chord internally
balanced ailerons on an NACA 65(112)- -213 airfoil. One of the

ailerons tested was of true airfoil contour and the other was
modified by partly eliminating the cusp near the trailing edge:_
Tests were made to determine the effects of the aileron contour_ _:
modification on the section aerodynamic characteristics of the
airfoil and aileron. ' '-

The results of the investigation indicated that_the __
modification to the aileron contour caused the aileron effective:
ness to increase slightly at low aileron deflections and to
decrease slightly at large aileron deflections; caused the rate
of change of aileron section hinge—moment coefficient with both
section angle of at tack and aileron deflection to increase
positively; caused little change in the hinge—moment parameter
for a given rate of roll at the low ailerOn deflections but an
increase in the hinge—moment parameter for a given rate of
roll at the high aileron deflections; caused no appreciable
change in the section drag coefficient, rate of change of
section lift coefficient with section angle of_attack,_and air—
foil criiical Mach number; and caused an increase of approxi-
mately 9 percent in the maximum section lift coefficient_of_the
airfoil with the ailerons neutral. The application of standard
roughness to the leading edge_of the airfoil increased positively _
the rate of change of aileron section hinge—moment__ coefficient ‘
with both section angle of attack and aileron deflection, decreased
the aileron effectiveness throughout the aileron deflection
range, and caused a smaller change in the hingeamoment_ parameter
for the true—contour aileron at any given rate of roll than for
the modified aileron. Aileron deflections of —3° and 3° were
found to have no significant effect on the airfoil.criticel
Mach number at the design section lift coefficient.