Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds /

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.An investigation has been made in the Langley high-speed 7-by 10-foot tunnel to determine some effects of tail height and wing plan form on the static longitudinal stability characteristics of a complete, small-scale model at high subsonic speeds. The model had both a low-tail position (wing chord plane extended) and a high-tail position (65 percent semispan above the wing chord plane extended). The wings were 4 percent thick, had an aspect ratio of 3, and had various taper ratios and angles of sweep. Three wings had a taper ratio of 0.50 and qusrter-chord sweep angles of 25, 30, and 35 degrees; whereas the fourth wimg had 30 degrees of sweep and a taper ratio of 0.20. The Mach number range extended from about 0.80 to 0.94 with corresponding Reynolds numbers ranging from about 1,170, 000 to 1,290,000 for average test conditions."August 25, 1954."Includes bibliographical references (p. 10).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.An investigation has been made in the Langley high-speed 7-by 10-foot tunnel to determine some effects of tail height and wing plan form on the static longitudinal stability characteristics of a complete, small-scale model at high subsonic speeds. The model had both a low-tail position (wing chord plane extended) and a high-tail position (65 percent semispan above the wing chord plane extended). The wings were 4 percent thick, had an aspect ratio of 3, and had various taper ratios and angles of sweep. Three wings had a taper ratio of 0.50 and qusrter-chord sweep angles of 25, 30, and 35 degrees; whereas the fourth wimg had 30 degrees of sweep and a taper ratio of 0.20. The Mach number range extended from about 0.80 to 0.94 with corresponding Reynolds numbers ranging from about 1,170, 000 to 1,290,000 for average test conditions.Mode of access: Internet