FIELD: aviation.
SUBSTANCE: proposed is an air intake of a supersonic civil aircraft located above the wing of the aircraft, made with a fixed angle of braking surface (4). Braking surface (4) is made in form of dihedral angle with smooth conjugation of planes-sides of dihedral angle. Boundary layer control system includes transverse slot (12) for removal of the boundary layer from the air intake channel, cavity (13) made in the under-panel space, openings for air discharge from the cavity into the external flow, as well as a window on the channel wall behind the air intake inlet and cutting the upper part of the air intake shell.
EFFECT: higher efficiency and gas-dynamic stability of the power plant.
3 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SUPERSONIC AIRCRAFT | 2020 |
|
RU2753443C1 |
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|
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| SUPERSONIC AIRCRAFT (VERSIONS) | 2007 |
|
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| SUPERSONIC INTAKE | 2007 |
|
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| ASYMMETRICAL AIR-SCOOP FOR THREE FLOW ENGINE OF FASTER-THAN-SOUND AIRCRAFT | 2018 |
|
RU2670664C9 |
| AIR INTAKE WITH VARIABLE GEOMETRY FOR SUPERSONIC AIRCRAFT (VERSIONS) | 2007 |
|
RU2353550C1 |
