The rolling effectiveness of a partial-span, perforated spoiler on a wing having 45° of sweepback has been determined at Mach numbers from 0.25 to O.96. The effects-of the spoiler on the lift, drag, and pitching moment were also determined. The spoiler had an average projection of 6.3 percent of the local wing chord and a span of 24.6 percent of the wing semispan. The wing had 45° of sweepback of the leading edge, an aspect ratio of 3, and a taper ratio of 0.4. The thickness-chord ratio parallel to the plane of symmetry was 0 03. The majority of the data were obtained at a test Reynolds number of 1,500,000; however, at a Mach number of 0.25 the Reynolds number was varied from,1,500,000 to 6,000,000.
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