Wind-tunnel investigation on the effect of a crescent planform on dragLift and drag forces were compared for elliptic and crescent wing models at cruise and climb conditions in the NASA/Langley 14 x 22-ft subsonic tunnel. The force measurements were obtained for an angle-of-attack range from -3 to 10 deg at a Reynolds number of about 1.7 million. The results indicate that for attached flow conditions, the crescent wing with its highly swept tips generates less lift-dependent drag than the elliptic wing for given lift force, wing span, and freestream conditions. The drag reduction is thought to be the result of the favorable influence of trailing wake deformations on the pressure distribution of the highly swept outboard region of the crescent wing.
Document ID
19900035141
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Van Dam, C. P. (California, University Davis, United States)
Vijgen, P. M. H. W. (High Technology Corp. Hampton, VA, United States)
Holmes, B. J. (NASA Langley Research Center Hampton, VA, United States)