FIELD: aviation.
SUBSTANCE: in the air intake power unit device of the hypersonic aircraft, comprising a stepped horizontal wedge of braking, an external shell and an internal partition forming two flow paths, one of the flow paths - centre - is composed of two channels of rectangular cross-section, formed by two stepped horizontal wedges of braking, two outer flat shells and two internal partitions, which are simultaneously the inner walls of two side channels of semi-circular cross-section of other flow path formed by two stepped cones of braking and two outer semi-circular shells.
EFFECT: improving the reliability of the device operation.
4 dwg
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