AIR INTAKE WITH VARIABLE GEOMETRY FOR SUPERSONIC AIRCRAFT (VERSIONS) Russian patent published in 2009 - IPC B64D33/02 

FIELD: aircraft industry.

SUBSTANCE: invention refers to aircraft industry, and namely to supersonic aircraft air intake design. Air intake with variable geometry for supersonic aircraft consists of a spatial wedge, a shell with a curved front edge and converging deceleration surface, side walls, drain system of boundary layer in air intake throat through a slot or perforations and curved subsonic diffuser. Channel after air intake throat is made in the form of rectangular cross-section at the inlet, and passes into curved subsonic diffuser with circular cross-section at the outlet. On air intake shell consisting of converging deceleration surface and rotating panels being the continued part of the shell, there installed are hinges ensuring rotation of panels in vertical plane and tightness of air intake channel. According to the second version, channel after air intake throat is made in the form of rectangular cross-section at the inlet, and passes into divergent supersonic diffuser of conical shape with broadening along its axis inclined in relation to longitudinal X axis coinciding with incoming flow direction.

EFFECT: providing effective air flow deceleration in conformity with existing standards, and uniform distribution of flow parameters in diffuser outlet section.

2 cl, 6 dwg