This paper discusses the effects of winglets (described in NASA TN D-8260) on the aero¬dynamic forces and moments, loads, and crossflow velocities behind the wing tip. The results of the investigation indicate that winglets significantly reduce the drag coefficient at lifting con-ditions. The experiments were conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.70 to 0.83 and over a lift coefficient range up to 0.65. A semispan model was used.
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