ADJUSTABLE SUPERSONIC AIR INLET

The invention relates to aeronautical engineering and, more specifically, to air intakes for supersonic aircraft propulsion systems. The technical result to be achieved by the invention consists in ensuring stable operation of the engine in all flight regimes up to the maximum Mach number of M=3.0 by adjusting the apex angle of stages of one of swept wedges and minimum area of the flow passage of the air intake. An adjustable supersonic air intake comprises an entrance in the form of a flow deceleration system - a supersonic diffuser (22) consisting of two multi-stage swept decelerating wedges (7) and (20) which form a dihedral angle; a shell, which also forms a dihedral angle, all edges of the entrance lying in the same plane; an air intake throat situated downstream of the deceleration system, and a subsonic diffuser (23), downstream thereof. As seen from the front, the entrance of the air intake has the shape of a rectangle or a parallelogram. The number of stages on swept wedges (7) and (20) may be different and the sweep of the wedges may be different from each other and from respective edges of the entrance. With the exception of the first stage, all of the stages of one of the two multi-stage swept wedges (7) and (20) are rotatable about an axis situated at the intersection of the first and second stages of the wedge, forming a movable front panel (11). A movable rear panel (12) is situated in the subsonic diffuser.