Aircraft comprising a fuselage to which wings (18, 20) are associated, leading edge extensions at the wing roots, at least one air intake for an engine and an engine, and a nose with a tapered section, in which said aircraft comprises control devices of the vortices generated by the wing leading edge root extensions, in which the ratio between the surface of one leading edge extension and the height of the corresponding control device is 2,35m with a variable tolerance in a range from 100% and -50% of such ratio, therefore comprised between 1,175 and 4,70 m, said control devices cooperating with the tail (44 and 38); wherein said aircraft also comprises a removable equipment comprising at least one dissipating device of incident radar waves which is applied in a removable way on at least one hot portion of the aircraft; hot portions of the aircraft being the following: - a piloting cabin or cockpit, comprising at least one transparent portion; - a first frame of the fuselage; - a plurality of leading edges of the components, comprising wings, tail planes and air intakes of the engines; - at least one engine face; the aircraft being characterized in that the removable equipment, in order to reduce the radar marking coming from at least one engine face, comprises at least one grid comprising an inner structure with a plurality of apertures; a support structure comprising a plurality of rings for securing said grid to the aircraft; wherein said plurality of apertures are realized having dimensions to be like a plane surface for the lowest frequencies of the frequency spectrum used by low-frequency radar recognition system; wherein each aperture comprises an internal surface coated with thin radar absorbing material adapted to absorb electromagnetic waves at high frequency; wherein said grid is adapted to permit the entry of an air flow towards the engine and reduce the visibility of engine face of aircraft by radar system; said grid has a circular shape similar to the cross section of the structure of the engine compartment; wherein said support structure comprises a first ring structurally bound to the duct of air intake of the engine, a second ring bound to a fireproof bulkhead comprised in the engine compartment, and a third ring, blocking a gasket interfaced with the engine. - a piloting cabin or cockpit, comprising at least one transparent portion; - a first frame of the fuselage; - a plurality of leading edges of the components, comprising wings, tail planes and air intakes of the engines; - at least one engine face; the aircraft being characterized in that the removable equipment, in order to reduce the radar marking coming from at least one engine face, comprises at least one grid comprising an inner structure with a plurality of apertures; a support structure comprising a plurality of rings for securing said grid to the aircraft; wherein said plurality of apertures are realized having dimensions to be like a plane surface for the lowest frequencies of the frequency spectrum used by low-frequency radar recognition system; wherein each aperture comprises an internal surface coated with thin radar absorbing material adapted to absorb electromagnetic waves at high frequency; wherein said grid is adapted to permit the entry of an air flow towards the engine and reduce the visibility of engine face of aircraft by radar system; said grid has a circular shape similar to the cross section of the structure of the engine compartment; wherein said support structure comprises a first ring structurally bound to the duct of air intake of the engine, a second ring bound to a fireproof bulkhead comprised in the engine compartment, and a third ring, blocking a gasket interfaced with the engine.