AERODYNAMIC CHARACTERISTICS OF TAPERED WINGS HAVING ASPECT RATIOS OF 4, 6, AND 8, QUARTER-CHORD LINES SWEPT BACK 45°, AND NACA 63-^012 AIRFOIL SECTIONS TRANSONIC-BUMP METHOD

摘要

As part of a transonic research program conducted by the National Advisory Committee for Aeronautics, a series of wings is being investi-gated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.15 by use of the transonic-bump technique.nThis paper presents lift, drag, pitching-moment, and root-bending-moment data of wings having aspect ratios of 8, 6, and 4, quarter-chord lines swept back 45°, and NACA 631A012 airfoil sections parallel to the plane of symmetry. The wings having aspect ratios of 6 and 4 were obtained by removing portions of the tip of the wing having an aspect ratio of 8 and, therefore, the taper ratios were 0.45, 0.56, and 0.68.nAll three wings, and especially the wing having an aspect ratio of 8, were characterized at low lifts by large reductions in lift-curve slope and very large forward movements of the aerodynamic center in the Mach number range from about 0.85 to about 1.0. However, above a lift coefficient of about 0.10 the pitching-moment characteristics as a function of Mach number were considerably better especially for the wing having an aspect ratio of 4. All three wings had a rather gradual drag rise starting in the Mach number range from about 0.90 to about 0.95.