FIELD: aviation.
SUBSTANCE: invention relates to power plants of aircraft. Supersonic convergent air intake of mixed compression includes external compression section with surface of external compression (1) made in the form of arc-like cross-section of bucket convergent surface sharpened in front, along front edge of nose. Internal compression section with internal compression surface (2) has a round cross-section. At the same air intake is made in the form of two combined identical parallel air intakes connected to each other in horizontal plane. Each air intake is made with its engine channel. Channels form in longitudinal plane of symmetry of aircraft, in place of attachment of external compression sections touching each other, internal central longitudinal vertical rib in the form of a longitudinal wedge of "seagull" shape with positive V with common nose for both air intakes in upper central part of air intake.
EFFECT: invention reduces drag, increases lift and improves stabilization.
3 cl, 9 dwg
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