Appeal 2007-0118
Application 10/175,612
increased base drag that offsets gains otherwise afforded by these
airfoil designs (Allen, col. 2, ll. 1-19).
11. Allen discloses adding a splitter plate to the blunt trailing edge to
reduce the base drag (Allen, col. 2, ll. 20-25).
12. Allen teaches that lift may vary across the span of a wing due to the
twist of a wing about its spanwise axis and changes in its camber, and
that near the tip of many wings, the lift approaches a minimum value,
and at 60% of the distance between the wing root and wing tip, the
wing has the maximum lift (Allen, col. 5, ll. 19-29).
13. As such, Allen teaches varying the height, h, at which the splitter plate
is attached to the blunt trailing edge to optimize the drag reducing
effect across the span (Allen, col. 5, ll. 30-43).
14. Vijgen teaches connecting a serrated panel 30 to the trailing edge 24
of an airfoil (Vijgen, col. 3, ll. 49-50).
15. Vijgen teaches that “the depth, planform shape and thickness of the
serratia can vary in the span-wise direction as a function of the wing
planform shape, wing twist distribution, and wing-tip shape” (Vijgen,
col. 4, ll. 41-44).
16. Vijgen provides examples of shapes of serrations in Figures 4 and 6-9
and states that size and shape of the serrations “may be varied
according to aerodynamic and geometric parameters of the airfoil”
(Vijgen, col. 5, ll. 20-22).
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