Abstract: The present invention increases the recovery ratio of air intake (AI) as the supersonic flight speed increases, by preventing the penetration of a non-decelerated flow into the channel. In a subsonic regime, all the tiltable panels (5, 8, 20 and 11, 12, 21) are located in a uniform flow and operate as vanes. The partitions serve as a guiding apparatus. In a supersonic regime, the pressure at the outer side of panels 5, 8, 20, which are adjacent to the profile of an expanding channel, is decreased. This decrease in pressure contributes to the panel rotation as the pressure increases in the boundary layer (b.l.) when the AI is throttled, wherein this pressure can be transmitted via a special channel 22. When the panels 11, 12, 21 are at the boundary of zones with different pressures, they are turned thereby forming an aerodynamically efficient shape of a subsonic channel.