A rear assembly of an aircraft turbojet engine nacelle , the rear assembly extending along a longitudinal central axis (A) and the rear assembly including a thrust reverser with sliding cascades which comprises at least: - a sliding cowl which is axially mounted movable in longitudinal translation from front to back, between a closing position in which the sliding cowl ensures the aerodynamic continuity of the nacelle , and an opening position in which the sliding cowl opens a passage for the redirection of an air flow coming from a cold air flow path of the nacelle , and - a cascade vane comprising a plurality of blading rows which each extend about the central axis (A) and which are arranged longitudinally from a first front blading row to a last rear blading row , each blading row including at least one deflection blade of the air flow towards the outside of the rear assembly of the nacelle , the cascade vane being secured in displacement to the sliding cowl , characterized in that the cascade vane includes at least one additional neutral blading row which is interposed between the last blading row and the sliding cowl and which includes at least one neutral blade , the neutral blading row delimiting a leakage passage towards the outside of the rear assembly of the nacelle which is designed so that the force exerted on said neutral blade by the air through the leakage passage is devoid of an axial component oriented backwards, and in that the leakage passage is delimited by a first rear face which extends radially and which belongs to the neutral blade and by a second front face which extends radially and which belongs to the blade of the last blading row , the first rear face and the second front face delimiting the leakage passage extending strictly radially. - a sliding cowl which is axially mounted movable in longitudinal translation from front to back, between a closing position in which the sliding cowl ensures the aerodynamic continuity of the nacelle , and an opening position in which the sliding cowl opens a passage for the redirection of an air flow coming from a cold air flow path of the nacelle , and - a cascade vane comprising a plurality of blading rows which each extend about the central axis (A) and which are arranged longitudinally from a first front blading row to a last rear blading row , each blading row including at least one deflection blade of the air flow towards the outside of the rear assembly of the nacelle , the cascade vane being secured in displacement to the sliding cowl , characterized in that the cascade vane includes at least one additional neutral blading row which is interposed between the last blading row and the sliding cowl and which includes at least one neutral blade , the neutral blading row delimiting a leakage passage towards the outside of the rear assembly of the nacelle which is designed so that the force exerted on said neutral blade by the air through the leakage passage is devoid of an axial component oriented backwards, and in that the leakage passage is delimited by a first rear face which extends radially and which belongs to the neutral blade and by a second front face which extends radially and which belongs to the blade of the last blading row , the first rear face and the second front face delimiting the leakage passage extending strictly radially. <EOS>