FIELD: aviation.
SUBSTANCE: invention relates to the aviation equipment. Aircraft wing comprises center section and cantilever, extension elongation λ = 8…11, narrowing η = 3.0…4.5, and comprises supercritical profiles. Leading edge in range from 0 to 25 % of the wing span is made with a break and an influx. Posterior edge is rectilinear. Front edge in area of 25…100 % has sweep −10…−15, and rear edge has sweep −15…−25. Relative thicknesses of wing profiles vary from 14…18 % in onboard cross-section to 9…12 % in wing end sections with geometric twist distribution law changing from ε = -1.0…-1.5° in onboard sections to ε = 1.5…2.0° in end cross-sections.
EFFECT: invention is aimed at reduction of resistance value.
3 cl, 4 dwg
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