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美国政府科技报告
>WIND-TUNNEL INVESTIGATION OF THE EFFECT OF CLIPPING THE TIPS OF TRIANGULAR WINGS OF DIFFERENT THICKNESS, CAMBER, AND ASPECT RATION – TRANSONIC BUMP METHOD
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WIND-TUNNEL INVESTIGATION OF THE EFFECT OF CLIPPING THE TIPS OF TRIANGULAR WINGS OF DIFFERENT THICKNESS, CAMBER, AND ASPECT RATION – TRANSONIC BUMP METHOD
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.O were tested. The tips of these wings were pro¬gressively 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-to-chord ratios of 0.02, 0.04, and 0.06. Wings having the NACA 63A(1.5)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.nIn general, the greatest decrease in drag-rise factor appeared with the change in taper ratio from 0 to 0.1
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