Abstract: An axially semisymmetrical supersonic air intake comprises a semiconical reaction engine displacer body having an air gap between the flat bottom of the air intake of the displacer body in the outer contour adjacent thereto of a missile or aircraft. The body transmits the boundary flow of the missile or aircraft and is bridged by a boundary layer plow. The body has a circumferentially distributed aperture on its surface in a zone of external normal shock which is produced during the subcritical conditions oscillating back and forth by which communication is established with the bleed air channel. The bleed air channels lead openings in the body to the flat bottom and may be subdivided by partitions in the interior of the body into individual parallel passages. The channels are formed by semiconical air baffles which are coaxial with the displacer body and taper in a direction opposite to the taper of the displacer body.

Abstract: A device, particularly for use with guided missiles, of a type having an intake pipe which is not fully rotationally symmetrical and is particularly semi-rotationally symmetrical, having particularly a semi-rotationally symmetrical air intake cross-section. The device prevents hum in the supersonic intakes of air-breathing reaction engines, particularly, ram jet engines, of a type which are operated with solid fuels and without regulation of the amount of air intake, the amount of fuel or the amount of thrust current flow for driving guided missiles. The construction includes a missile body having an intake pipe mounted thereon with a front opening disposed in an opening plane defining an inlet. A displacement body is mounted within the pipe in spaced relationship thereto and has a front pointed end which extends outwardly beyond the intake plane and which projects into the incoming air flow.