Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop Page: 4 of 24
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NACA RM L54LI0 5
M Mach number
M-/4 pitching moment about E/4, in-lb
Pb base pressure coefficient, PbPo
q
Pb static pressure at model base, lb/sq ft
Po free-stream static pressure, lb/sq ft
q dynamic pressure, pV2/2, lb/sq ft
R Reynolds number based on c
S wing area, sq ft
V free-stream velocity, ft/sec
a angle of attack of fuselage center line, deg
ACD,ACL,ACm incremental coefficients produced by leading-edge
droop, coefficient for wing with 60 droop - coeffi-
cient for plane wing
p free-stream density, slugs/cu ft
MODEL AND APPARATUS
The tests were conducted in the Langley 16-foot and 8-foot transonic
tunnels, which are described, respectively, in references 3 and 4. Two
models of steel construction which were geometrically similar, except
for a slight modification of the fuselage afterbody, were used. In the
16-foot-tunnel tests a large model provided data at a Reynolds number of
about 6 x 106; in the 8-foot-tunnel tests a model one-third as large
provided data at a Reynolds number of 2 x 106. The models were attached
to their respective tunnel sting support systems by means of internal
strain-gage balances; six force and moment components were measured in
the 16-foot tunnel and three in the 8-foot tunnel. The wings of the
models had 45 sweepback of the quarter-chord lines, a taper ratio of 0.6,
an aspect ratio of 4, and basic NACA 65A006 airfoil sections parallel to
the plane of symmetry. Camber was obtained by drooping the leading edge
of the wings 6o about the 19-percent-chord line from 0.15 sedispan to the
wing tip. The maximum value of the mean-line ordinate was about 2 percent
of the chord and was measured from the chord line between the leading
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Schmeer, James W. & Cooper, J. Lawrence. Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop, report, February 4, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61152/m1/4/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.