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• August 26, 2016 Create Date
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National Advisory Committee for Aeronautics, Report - Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack, VI - Skewed Ailerons on Rectangular Wings

This report covers the sixth of a series of investigations
in which various lateral control devices are compared im'th
particular reference to their efi'eetiveness at high angles of
attack. The present report deals with flap-type ailerons
hinged about axes having an angle with respect to the
leading and trailing edges of the wing. Tests were made
on four diflerent skewed ailerons, including two diflerent
angles of skew and two sizes of ailerons. At the high
angles of attack, all the skewed ailerons tested were slightly
inferior with respect to rolling and yawing moments to
straight ailerons having the same span and average chord.
Computations indicate that the skewed ailerons are also
inferior with respect to hinge moments.
This report is the sixth of a series giving the results
of an investigation in which it is hoped to compare
all types of lateral control devices which have been
satisfactorily used or which show reasonable promise of
being effective. In this program it is planned first to
test the various types of ailerons and other control
devices on rectangular wings of aspect ratio 6. Later
the best of these control devices are to be tested on
wings of different shape. In the entire series the vari—
ous devices are to be subjected to the same program of
Wind-tunnel tests which, it is thought, include all the
factors directly connected with lateral control and
stability that can be satisfactorily handled in a routine
manner in a wind tunnel. The tests are designed to
show the relative merits of the various control devices
in regard to lateral controllability, lateral stability,
and general usefulness. They include regular 6-com-
ponent force tests with the control devices both neutral
and deflected various amounts, rotation tests in which
the model is rotated about the tunnel axis and the
rolling moment measured, and free rotation tests show-
ing the range and rate of autorotation. Because of the
large effect of yaw on lateral stability, the tests are
made not only at 0° yaw, but also with an angle of
yaw of 20°, which represents the conditions in a
fairly severe sideslip.