FIELD: aircrafts.
SUBSTANCE: invention relates to aircraft. The air intake device of a supersonic aircraft comprises a central body (1), a shell (2), a profiled leading edge (3) forming an inlet (4) of the air intake device and an air intake channel. The central body (1) is formed by side surfaces (5) and a stagnation surface (6) obtained from a reverse conical flow notch.
EFFECT: increase in the efficiency of the propulsion system in various speed modes is achieved while maintaining overall and layout characteristics.
1 cl, 3 dwg
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|
RU2287456C1 |
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| MISSILE WITH AIR-JET ENGINE | 2015 |
|
RU2585211C1 |
