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An investigation has been conducted to determine the effect of conical camber on the drag due to lift and on the static longitudinal, lateral, and directional stability characteristics of an aspect-ratio-3, 45 degree sweptback wing in combination with a streamline body. Tests were made at Mach numbers up to 0.96 at a Reynolds number of 1.5 million and at a Reynolds number up to 8 million at a Mach number of 0.22, both with and without roughness strips near the leading edge of both the upper and lower surfaces of the wing.