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National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack - VIII - Handley Page Tip and Full Span Slots with Ailerons and Spoilers

This report is the seventh in a series of systematic
tests in which various lateral control devices are com— _
pared with particular reference to their effectiVeness at
high angles of attack. The present tests were made with
ordinary ailerons and different sizes of spoilers on rec—
tangular Clark Y wing models with Handley Page tip and
full—span slots. The tests, which were made in the 7 by
10 foot wind tunnel of the National Advisory Committee
for Aeronautics, showed the effect of. the control devices
on the general performance of the wings as well as on the
lateral control and lateral stability characteristics.

It was found that the wing with Handley Page tip '
slots and certain combinations of the ailerons and prop-
erly located spoilers had satisfactory damping in roll
and satisfactory rolling control with no adverse yawing
moments at angles of attack up through 30° _With the
full—span slot the conventional ailerons alone did not
give rolling control of an assumed satisfactory amount at
angles of attack above 10° (maximum lift occurred at 26°),
but when combined with spoilers satisfactory rolling.@9'
ments were obtained—with no adverse yawing moments. Large
spoilers tested* as_ the so_le means of lateral control on
both the wing with tip Slots and that with the full—span
slot gave in both cases a moderate amount of rolling con—
trol at all angles of attack, together with favorable
yawing moments which were extremely large, possibly too
large.

A series of systematic wind—tunnel investigations is
being made by the National Advisory Committee for Aero—
nautics in order to compare various lateral Control de»
vices. -The various devices are given the same routine
tests to show their relative merits in regard to lateral
controllability and their effect on the lateral stabil—
ity and on airplane performance. They are being tested
first on rectangular Clark Y wings of aspect ratio 6, then
on wings with different plan forms, wings with high lift
devices, and also on wings with such variations as washout
and sweepback, which affect lateral stability. The first
report of this series (referenCe 1, Part I) deals with
three sizes of ordinary ailerons, one of these a medium~
sized one taken from the average of a number of conven»
tional airplanes and used as the standard of comparison
throughout the entire investigation.