Investigation of the effects of leading-edge flaps on the aerodynamic characteristics in pitch at Mach numbers from 0.40 to 0.93 of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4 Page: 2 of 38
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NACA RM L53G13 -r a" 3 1176 01437 1273
NATIONAL ADVISORY CCMITTEE FOR AERONAUTICS
INVESTIGATION OF THE EFFECTS OF LEADING-EDGE FLAPS ON
THE AERODYNAMIC CHARACTERISTICS IN PITCH AT MACE
NUMBERS FROM 0.40 TO 0.93 OF A WING-FUSELAGE
CONFIGURATION W A 450 SWEPTBACK WING
OF ASPECT RATIO 4
By Kenneth P. Spreemann and William J. Alf ord, Jr.
An investigation was made to determine the effects of a number of
leading-edge flaps on the aerodynamic characteristics in pitch of a wing-
fuselage configuration with a 450 sweptback wing of aspect ratio 4, taper
ratio 0.5, and NACA 65A006 airfoil section. The investigation was made
in the Langley high-speed 7- by 10-foot tunnel over a Mach number range
of 0.40 to 0.93 and an angle-of-attack range of about -20 to 240. Lift,
drag, and pitching-moment data were obtained for all configurations.
All the leading-edge flaps investigated reduced the drag in the
medium lift range. Full-span and outboard partial-span flaps deflected
30 or 60 usually gave better maximum lift-drag ratios than any of the
other leading-edge flap arrangements investigated throughout the - Mach
number range. In general. all leading-edge flaps delayed the sharp pitch-
up tendencies of this model by from 0.2 to 0.4 lift coefficient up to a
Mach number of 0.90, but provided little or no improvement at the highest
Mach numbers investigated.
Previous investigations at high subsonic speeds have shown that the
lift-drag ratios of low-aspect-ratio sweptback wings could be substan-
tially improved with low-angle leading-edge flap deflections up to a Mach *
, number of 0.90 (refs. i and 2). As a result of these investigations study
of a more comprehensive range of full-span and partial-spa deflections
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Spreemann, Kenneth P. & Alford, William J., Jr. Investigation of the effects of leading-edge flaps on the aerodynamic characteristics in pitch at Mach numbers from 0.40 to 0.93 of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, report, August 20, 1953; (digital.library.unt.edu/ark:/67531/metadc59660/m1/2/: accessed November 15, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.