FIELD: aviation.
SUBSTANCE: invention relates to the aviation equipment. Aircraft wing consists of center section and cantilever, is swept χ=-20÷-40° and comprises supercritical profiles. Relative thickness of profiles has value of 10 % in onboard cross section and decreases to 7÷8 % in end section, monotonously decreasing on section from 0 to 80 % of span. Wing is designed with positive swirling ε=0÷0.1° in onboard section. In sections the center section has negative twist ε=-0.2÷-1.5°. Console sections are designed with change of swirling from 3° up to ε=-1.6÷-2.0° and contain end surfaces with positive sweep.
EFFECT: invention is aimed at improvement of technical and operational characteristics.
1 cl, 5 dwg
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Authors
Dates
2020-01-17—Published
2019-04-01—Filed