• Version
• 130 Downloads
• 1.08 MB File Size
• 1 File Count
• November 30, 2016 Create Date
• November 30, 2016 Last Updated

National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Investigation of Effect of Yaw on Lateral Stability Characteristics - III - Symmetrically Tapered Wing at Various Positions on Circular Fuselage With and Without a Vertical Tail

Model combinations of an NAOA 23012 tapered wing and
a circular fuselage were tested in the NAGA 7- by 10-foot
wind tunnel to determine the effect of longitudinal wing
position on the change in lateral stability due to inter-
ference. The aerodynamic center of the wing was located
at approximately 80, 130, and 180 percent of the mean
chord from the nose of the fuselage. At each of thBSe
locations, the model was tested as a high-wing, a midwing,
and a low-wing-monoplane. -For each combination, tests
were made with a partial-span split flap neutral and de—
flected 60° and with and without a vertical tail. The
rearmost low-wing combination was tested with and without
a fillet-

The results are presented in the form of charts
showing, for each combination. the increments_of;the
slepes of the curves of the rolling-moment, the yawing-
moment. and the lateral-force coefficients against yaw
due to wing-fuselage interference. Contours are also
given that show the variation at zero angle of attack of
these increments with the position of the wing on the
:fuselage. .

The longitudinal position of the wing was found to
have very little effect on the wing-fuselage interference
as compared with vertical position. The wing—fuselage
interference tended in most cases to decrease the effec-
tive dihedral as the wing position was changed longitudi-
nally; of the three longitudinal locations tested, the_
maximum effective dihedral was obtained at the central
position. The effect of the wing-fuselage interference
on directional stability increased favorably when the

wing location was moved forward. The influence of wing—
fuselage interference on the directional stability con-
tributed by the vertical tail was beneficial for the low-
wing combination and detrimental for the high-wing com—
bination and this influence increased as the wing posi-
tion was moved rearward. The fillet prevented sudden
changes in the lateral-stability characteristics of the
low—wing model at high.angles of attack below the stall
by delaying the occurrence of the burble at the wing-
fuselage Juncture.