FIELD: aviation.
SUBSTANCE: invention relates to subsonic aircraft wings. Aircraft wing consists of center wing and cantilever, extension λ=8÷11, narrowing η=3.0÷4.5 and has supercritical profiles. Front edge when viewed from the top in range from 0 to 25 % of the wing span is made with a fracture and an influx, the trailing edge is rectilinear, relative thicknesses of wing profiles vary from 15÷17 % in onboard cross section up to 10÷11 % in wing end sections, with the geometrical twist distribution law varying from span of 0.0–0.5° in board sections to -0.1÷-1.0° in end sections. Wing allows increasing maximum aerodynamic quality. ΔQmax≈0.1÷1.1 and improve fuel efficiency by 3÷7%.
EFFECT: invention is aimed at improvement of takeoff and landing characteristics in the absence of a slat and providing natural laminarisation of the streamlining of the surface.
1 cl, 4 dwg
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