Abstract
Results from lifting line theory, vortex lattice methods, and Euler techniques suggest that simple spanwise cambering of a planar wing, resulting in a reduced projected span but equivalent arc length and area, reduces the induced drag. Lifting line theory suggested a reduction of induced drag in positive cambered wings by almost 1% for certain configurations. Three-dimensional Euler flow solutions were obtained using the TetrUSS package from NASA Langley and suggested a drag reduction of as much as 1.6%, or 4.3 drag counts for the current configuration, with upward cambered wings. Viscous solutions were also run on the optimum Euler geometry and indicated reduced improvements of less than 1 count or 0.30%. Initial optimization with twist improved the Euler results to 2%.
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