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National Advisory Committee for Aeronautics, Research Memorandum - Rolling Effectiveness of All Movable Wings at Small Angle of Incidence at Mach Numbers from 0.6 to 1.6

Experimental data have been obtained of the rolling effectiveness
of several all-movable wing configurations by means of rocket-propelled
test vehicles in free flight. The results are compared with some avail-
able methods of estimation. These results validate the use of the simple
equation derived by a strip integration and originally presented in
NACA RM L50Glll-b over a wide range of application as a means of estimating
the rolling effectiveness of all-movable wings.

The wing—control effectiveness data obtained by the Langley
Pilotless Aircraft Research Division are normally presented for models
having zero wing incidence. The data Obtained from models having small
but measurable wing incidence resulting from practical construction
tolerances must therefore be corrected to a nominal average wing inci—
dence value of zero. The experimental data presented herein were pri-
marily obtained for the purpose of verifying the use of the equation
(derived in the appendix) which was originally presented in
reference 1 as a means of correcting rolling effectiveness to
zero incidence. Inasmuch as the current investigation related to the
problem of predicting rolling effectiveness of aircraft configurations
having all-movable wings, a comparison is made of the pb/2V values
estimated from strip theory and the estimated values from references
2, 3, and h with the experimental values of this investigation. These
three methods of estimating the pb/2V' values for various Mach numbers
are also compared with similar experimental data obtained by a different
technique described in reference 2.

Three wing plan fonms were testedJ an untapered wing_having 00 and _
1:50 sweep and a delta wing having a 15° swept leading edge_._ (It is con—i
sidered that these plan forms represent a sufficiently wide range for
assuming that the demonstrated agreement with the simplified incidence
correction theory should hold true for wings with plan forms intermediate
to those for which data are available.)

All experimental data presented in this paper, excluding the exper—A:
imental data taken from reference 2, were Obtained by means of rocket—
propelled test vehicles in free flight.