WIND-TUNNEL INVESTIGATION OF THE EFFECT OF CLIPPINGnTHE TIPS OF TRIANGULAR WINGS OF DIFFERENT THICKNESS, CAMBER, AND ASPECT RATIO - TRANSONIC BUMP METHOD

摘要

The investigation reported herein was conducted on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms having aspect ratios of 2.0, 2.5, 3-0, and 4.0 were tested. The tips of these wings were progressively clipped to provide taper ratios of 0.1, 0.2, 0.3, 0.4 and in some cases 0.5. The NACA 63AOOX profile was used with thickness-tochord ratios of 0.02, 0.04, and 0.06. Wings having the NACA 63A (l.5)04 section were also investigated for each aspect ratio. Data were obtained over a Mach number range from 0.60 to 1.10 corresponding to a test Reynolds number range from 1.85 million to 2.90 million. Lift, drag, and pitching-moment coefficients are presented for each of the wings investigated.