FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering. Perforated structure of aircraft skin with combined openings and damping cavity comprises outer skin having plurality of spatially distributed perforated openings, flowing through it, configured to affect air flow thereof, including air flow of boundary layer extending along outer surface. Upper and lower surfaces of skin include combined perforated openings of different geometric shapes with different orientations on surface and below unvoiced damping cavities. Combined openings of various geometries can have combination of complex and simple figures and be directed along leading edge of wing and tail-plane.
EFFECT: invention is aimed at reducing scrubbing drag.
4 cl, 12 dwg
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