ENTREE D'AIR SUPERSONIQUE EN DEMI-CORPS DE REVOLUTION POUR PROPULSEURS A REACTION, NOTAMMENT POUR MOTEURS-FUSEES DU TYPE STATOREACTEUR A PROPERGOLS SOLIDES

摘要

Half rotationally symmetrical supersonic air inlet with a semi-conical displacement element for reaction jet engines, especially for ram jet rocket engines, powered by solid fuels without mechanical control of the air inlet quantity and of the thrust flow for the propulsion of guided missiles and aircraft, an air gap being provided between the base surface of the air inlet and/or of the displacement element and the external contour of the missile or aircraft adjacent to this base surface, which air gap admits the boundary layer flow of the said external contour and is bridged by a boundary layer plough, and an air exhaust device being provided on the surface of the displacement element in the area of the straight line thrust oscillating to and fro and run out in the sub-critical operating state. At the same time a separating plate in the form of a triangle acute-angled at the cone tip and extending from the cone tip of the displacement element into its exhaust area is arranged on each of the two lateral edges of the displacement element.