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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.
The lateral flow characteristics in the region of a vertical tail have been investigated experimentally and theoretically at low subsonic speeds. The effects of changes in wing-body geometry such as nose position and shape, fuselage cross-sectional shape, and wing vertical position are described. The theoretical model which approximates the separated flow phenomena by a simple cylinder-vortex flow is described in an appendix.