FIELD: aviation.
SUBSTANCE: natural laminar wing for supersonic aircraft, in which shape of cross section of wing along wing chord at each point along wing span is selected so that curvature near leading edge has a predetermined value 1/3 or less in comparison with normal cross-section in area of linear element 0.1 % of length of wing chord. Curvature in area of linear element 0.2 % of wing chord length from linear element to wing trailing edge is additionally decreased to 1/10. Required pressure distribution for top and bottom surfaces of wing is selected on basis of obtained pressure distribution.
EFFECT: invention is aimed at maximum displacement backwards downstream of turbulisation point.
6 cl, 12 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| PRODUCTION OF WING FOR AIRCRAFT WITH FUSELAGE BY CONFIGURING WING FOR EXTENSIVE LAMINAR AIRFLOW AND AIRCRAFT (VERSIONS) | 2010 |
|
RU2531536C2 |
| AIRCRAFT WING | 2019 |
|
RU2717416C1 |
| DEVICE FOR BODY FLOW-OVER LAMINARISATION | 2009 |
|
RU2400399C1 |
| WING WITH SUPERSONIC FREE LAMINAR FLOW (VERSIONS) AND WING SURFACE LAMINAR FLOW CONTROL SYSTEM | 1994 |
|
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| LIGHT AIRCRAFT WING | 2023 |
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RU2821105C1 |
| STREAMLINED BODY, PRIMARILY FOR AIRCRAFT | 2010 |
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RU2496680C1 |
| AIRCRAFT WING | 2019 |
|
RU2717412C1 |
| SUPERSONIC FLYING OBJECT NOSE | 2011 |
|
RU2570193C2 |
| AIRCRAFT WING | 1986 |
|
SU1840803A1 |
| WING OF SUBSONIC AIRCRAFT | 1990 |
|
RU1775972C |
