Abstract: Inlet cone (1) for a jet engine (10) configured as a bypass turbojet engine, which has an engine core area (11) and a casing area (12) that surrounds it, whereby the inlet cone (1) is placed concentrically in the air inlet area of the jet engine (10) and placed on a turnably supported shaft (14), whereby the inlet cone (1) has a conical angle (15) at which solid bodies (16) impinging with the air flow onto the inlet cone (1) ricochet off it in motion paths (17) which lead most of the solid bodies (16) into the casing area (12). Thereby an inlet cone (1) is created in which the entry of solid bodies 16 into the engine core area (11) can be minimized.