Wing for aircraft or hydrofoil

摘要

The wing has an aerofoil section, in which the position of maximum thickness (a), a profile index (n) for its forward part, and a profile index (p) for its rear part can be freely determined. The position of maximum thickness of the section, and the profiles of its front and rear parts can be optimised for given circumstances. The section profile can be defined in terms of its thickness (y-coordinate), varying with the position (x-coordinate) along the chord. The relationship is given as: y=b/aa<m>-(a-x)<m><n>, 0 <= x <= a (m<.>n=1) (yt-b){x-a/c-a)<p>+b, a <= x <= c