Turbojet nacelle air inlet comprising a deflection device to promote a thrust reversal phase

摘要

An air inlet (2) of an aircraft turbojet nacelle (1) extending along an X axis and comprising at least one deflection member (3, 4, 5) mounted to move between a deployed position, in wherein the deflection member (3, 4, 5) protrudes from the inner wall (21) or from the air inlet lip (23) in a radially inner direction of deployment facing the axis X or a longitudinal direction of deployment with respect to the X axis, in order to allow separation (D) of the reverse air flow (F-INV) from the inner wall (21) to promote the thrust reversal phase , and a retracted position, in which the air inlet (2) has an aerodynamic profile so as to guide the interior air flow (F-INT) on the interior wall (21) to promote the thrust phase. Abstract figure: Figure 3