Turbojet engine comprising a nacelle with an air intake to promote a reversed thrust phase

An aircraft turbojet engine extending along an axis X oriented from upstream to downstream in which an internal air flow circulates from upstream to downstream during a thrust phase and a reverse air flow from downstream to upstream during a thrust reversal phase, said turbojet engine comprising a fan configured to provide reverse thrust and a nacelle comprising an air intake, the air intake circumferentially extending about axis X and comprising an internal wall pointing to axis X and configured to guide the internal air flow and the reverse air flow, and an external wall opposite to the internal wall and configured to guide an external air flow, the internal wall and the external wall being connected to each other by an air intake lip so as to form an annular cavity, the air intake comprising a deflection device comprising at least one deflection member movably mounted between an extended position, in which the deflection member projectingly extends from the internal wall or from the air intake lip in a radially internal extension direction pointing to axis X or a longitudinal extension direction relative to axis X in order to allow a separation of the reverse air flow from the internal wall to promote the thrust reversal phase, and a retracted position, in which the air intake has an aerodynamic profile so as to guide the internal air flow onto the internal wall to promote the thrust phase.