| 摘要 |
<p>The present invention concerns an innovative wing (1) specific for an aircraft operating in the transonic regime and comprising: - A root section (2); - A tip section (3) and; - A leading edge (4) for connecting the root section to the tip section. In accordance with the invention, the curved leading edge (4) is configured according to a line by which locally the angle (?) formed by the forwarding direction of the wing and the perpendicular to the tangent of the leading edge increases progressively from the root section (2) to the tip section (3) of the wing (1). In such a way, the speed component (Vu) of the wing orthogonal to the leading edge decreases progressively from the root section to the tip section, thus reducing the local Mach number progressively.</p> |
