Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees Page: 2 of 43
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
AERODYNAMIC CHARACTERISTICS AT A MACH NUMBER OF 1.38
OF FOUR WINGS OF ASPECT RATIO 4 HAVING QUARTER-
CHORD SWEEP ANGLES OF 00, 30, 0, AND 600
By William B. Kemp, Jr., Kenneth W. Goodson,
and Robert A. Booth
A description of the Langley 6-inch supersonic tunnel is presented
together with results of tests conducted at a Mach number of 1.38 and a
Reynolds number of 390,000, to determine the supersonic aerodynamic
characteristics of four sweptback wings and wing-body configurations.
The wings were all of aspect ratio 4, taper ratio 0.6, and NACA
6SAO06 airfoil section. The sweepback angles used were 00, 350,. 45o
At the low Reynolds number of the present tests, laminar separation
occurred near the trailing edge of all wings producing reduced stability
in the low-lift range. The effects of increasing angle of sweepback
were to reduce the lift-curve slope and zero-lift drag coefficient, to
increase the maximum lift-drag ratio, and to produce an outward shift in
the lateral center of pressure. The measured lift-curve slopes were
less for all wings than those predicted from linearized theory. Good
agreement was obtained between theoretical and experimental aerodynamic-
center location in the lift-coefficient range not affected by separation
effects for sweep angles up to 450. For the 600 sweptback wing at lift
coefficients above 0.25, a leading-edge separation vortex produced
severe instability with reduced lift and increased drag. At lift coef-
ficients below 0.25, this wing exhibited a considerable proportion of
the theoretically available leading-edge suction. Addition of either
leading-edge roughness, blunt trailing edge, or a fence to the 600o wing
improved the stability characteristics at low lift coefficients. The
fence also decreased the instability of the 600 wing at high lift
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Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A. Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees, report, October 10, 1950; (https://digital.library.unt.edu/ark:/67531/metadc58552/m1/2/: accessed March 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.