| 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 fuel 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 of the air inlet and/or of the displacement element and the external contour of the missile or aircraft adjacent to this base, 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 displacement element in the area of the straight line thrust oscillating to and fro and run out in the sub-critical operating state, at least two frustum-shaped air baffle plates running backwards at an angle in the direction of flow being connected on the air release device, a front air baffle plate on the front boundary and a rear air baffle plate on the rear boundary of the exhaust device and where necessary other intermediate air baffle plates forming the air guide ducts, from which overflow openings in the base of the frustum-shaped displacement element lead into the internal chamber of the rear part of the boundary layer plough.
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