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: 4 of 38
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NACA EM L53G013 a
c mean aerodynamic chord of wing, ._ c2dy, ft
c local wing chord, parallel to plane of symmetry, ft
b wing span, ft
p air density, slugs/cu ft
V free-stream velocity, ft/sec
Po free-stream static pressure, lb/sq ft
Pb static pressure at base of model, b/sq ft
M Mach number
R Reynolds number of wing based on c
angle of attack of fuselage center line, deg
L, change in local angle of attack due to distortion of wing, deg
K correction factor for C due to wing distortion
C lift-curve slope, C
A- incremental change in aerodynamic-center location due to wing
y spanwise distance from plane of symmetry, ft
6n leading-edge flap deflection angle, deg (see fig. 1)
A leading-edge flap that extends from 0.139 b/2 to 0.426 b/2
B leading-edge flap that extends fran 0.426 b/2 to 0.713 b/2
C leading-edge flap that extends franom 0.713 b/2 to 1.00 b/2
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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/m1/4/: accessed December 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.