| 摘要 |
<p>This invention pertains to supersonic air intakes intended for aircraft jet engines. The self-adjusting air intake comprises a supersonic area, a neck, a subsonic area and at least one additional channel connecting the supersonic area to the subsonic area. At the entrance of the channel in the supersonic area a rotating panel is installed, its axis of rotation being situated downstream the flow. The design of the air intake increases the efficiency and reliability of operation over a broader range of flight speeds thanks to the self-adjustment of the flow-through portion to the current speed of the incoming flow and to the amount of back pressure.</p> |
