The results presented in the present paper represent a continuation of a research program conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations having variations in the wing geometric parameters. Presented herein are the aerodynamic characteristics in pitch of wing-fuselage combinations with wings having an aspect ratio of 4, a sweepback angle of 450, and taper ratios of 0.3, 0.6, and 1.0. The Mach number range was from 0.40 to about 0.95 and the Reynolds number range was from 2,000,000 to 3,000,000.
展开▼
