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aircraft wing with a system establishing laminar boundary layer flow
aircraft wing with a system establishing laminar boundary layer flow
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机译：具有建立层流边界层流的系统的飞机机翼
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摘要
patent summary: "aircraft wing with a system establishing laminar boundary layer flow". To establish a connecting line flow, the present invention proposes an aircraft wing (10) comprising: a leading edge (12), leading edge (12) including a connecting line (14) in a region where air, which reaches it, flows in the direction of the boundary layer span along the front edge (12), a first slat (22) and second slat (24), where the front edge (12) and the connecting line (14) at least partially formed in the first and second slats (22, 24), the second slat (24) being located adjacent to the first slat (22), downstream of the connecting line flow, so that the leading edge ( 12) includes a slat-with-slat junction (26), and a slat-cavity (30) is formed at the slat-with-slat junction (26) under the skin area (36) of at least one of the first and second ones. slats (22, 24), and a duct (38) having a duct inlet (40) at the slat-with-slat junction (26) to receive flow in the direction of the wingspan along the b front flange (12) of the wing (10), the duct (38) being formed at least partially by said slat cavity (30), wherein the duct inlet (40) extends around the front edge (12). ) and over a range of connecting line positions (14) at the slat-with-slat junction (26).
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