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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.
Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.