Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method Page: 3 of 32
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2 g NACA RM L51C16
INTRODUCTION
In the transonic and supersonic speed range one of the
promising configurations from a compromise between aerodynamic and
structural requirements is the swept wing of low aspect ratio with thin
airfoil section. A wing of this type has the advantage of low drag at
zero lift but this gain in performance is partly offset by high drag
due to lift. Previous investigations at subsonic and supersonic speeds
have shown that the lift-drag characteristics can be improved by
twisting and cambering the wing (references 1 and 2). To secure infor-
mation through the transonic speed range, two wings were investigated;
one was an untwisted, uncambered wing (hereafter referred to as a flat
wing) similar to one tested at subsonic and supersonic speeds (refer-
ences 3 and 4)_and the other had the same plan form but incorporated
twist and camber designed to give uniform loading at a Mach number
of 1.10 and a lift coefficient of 0.25.
This investigation was conducted in the Langley high-speed 7-
by 10-foot tunnel over a Mach number range between 0.68 and 1.15 which
was obtained by use of the transonic-bump method. Included in the
paper are the results of the investigation of the wings-alone and wing-
fuselage combinations. Lift, drag, pitching moment, and root bending
moment were obtained for these configurations.
COEFFICIENTS AND SYMBOLS
CL lift coefficient (Twice semispan lift/qS)
CD drag coefficient (Twice semispan drag/qS)
nC pitching-moment coefficient referred to 0.253
(Twice semispan pitching moment/qSc)
CB bending-moment coefficient about axis parallel to relative
wind in plane of symmetry (Root bending moment/q A)
q effective dynamic pressure over span of model, pounds per
square foot (-pv2)
S twice wing area of semispan model, 0.125 square footAL 6 r+
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Spreemann, Kenneth P. & Alford, William J., Jr. Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degrees 38 Minutes Sweptback Wing of Aspect Ratio 2.98: Transonic-Bump Method, report, August 27, 1951; (https://digital.library.unt.edu/ark:/67531/metadc58758/m1/3/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.