An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47 degrees sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Lang

Ralph P. Bielat, Daniel E. Harrison, Domenic A. Coppolino
naca-rm-l51i04a
Oct 1951


Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.

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