| 摘要 |
FIELD: supersonic aircraft. SUBSTANCE: invention relates to primary air intakes of power plants of supersonic aircraft. Inlet hole of air intake air channel is formed by front edges of shell walls. According to one design version, said edges are located in plane tilted through acute angle to longitudinal axis of air channel coinciding with direction of oncoming air flow. Part of shell walls, including two walls forming sharpened nose, are made wedge-like, with braking surfaces forming contraction of air channel on its section to neck of air intake over of shell perimeter on its frontal projection. Part of wedge-like walls is made with suction holes of boundary layer of braking air flow. Braking surfaces are arranged at different small angles in points of corresponding wedges. Non-wedge-like walls of shell on section after their front edges to neck of air intake are made straightline, being arranged in parallel with above-indicated longitudinal axis of air channel. According to other design version, front edges of shell walls are located in two planes intersecting in straight line passing through two noses formed by sharpening of corresponding opposite walls of shell at acute angle to longitudinal axis of air channel coinciding with direction of oncoming air flow. Noses of shell are displaced relative to each other, and parts of shell walls, including walls with sharpening, are made wedge-like with braking surfaces. EFFECT: reduced resistance of air intake, increased coefficient of restoration of full pressure. 7 cl, 6 dwg
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