The use of pure twist for drag reduction on arrow wings with subsonic leading edges

Frederick C. Grant
naca-tn-4104
Aug 1957


Linearized-theory calculations of the drag reduction achieved by applying the first three terms of a power series for twist to flat delta wings are presented. In addition, the reductions due to applying linear twist to a family of flat arrow wings are presented. The results cover the speed range of subsonic leading edges.

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