WIND-TUNNEL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS IN PITCH OF WING-FUSELAGE COMBINATIONS AT HIGH SUBSONIC SPEEDS TAPER-RATIO SERIES

摘要

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, side¬slip, and steady roll of model configurations having variations in the wing geometric parameters. Presented herein are the aerodynamic charac¬teristics in pitch of wing-fuselage combinations with wings having an aspect ratio of 4, a sweepback angle of 45°, 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.nThe results of the investigation indicate at low lift coefficients a reduction in lift-curve slope and a forward movement in aerodynamic center with an increase in taper ratio throughout the test range of Mach number, as would be predicted from available theory.