The damping—in-roll coefficients for a series of thin triangular plan-form wings and two rectangular wings have been obtained in the Langley 9-inch supersonic tunnel. The triangular-wing series consisted of nine wings of vertex angles such that a range of leading edge positions ahead of and behind the Mach cone was obtained at two Mach numbers, 1.62 and 1.92. The rectangular wings were of aspect ratio 2.00 and 2.73. All the wings were tested in the presence of a body of revolution.nIt was found that the damping in roll of the rectangular wings was very close to that predicted by linear theory for isolated wings.nThe triangular wings gave results approximately 10 percent below that predicted when the wing leading edges were well ahead of or behind. the Mach cone. Somewhat greater reductions in the damping coefficients from the linear theory were found when the leading edges were in the vicinity of the Mach cone.
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