Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

Abstract: An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.

Abstract: The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators.

Abstract: The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon (14) intended to be laterally attached on a rear portion of the structure of the aircraft, the pylon having an outer surface (20) forming an aerodynamic profile incorporating a trailing edge (21), the latter being arranged upstream of the propeller of the turboshaft engine. According to the invention, the pylon comprises a mobile rear flap (24) at least partially defining the trailing edge (21), as well as a control means (34) of the flap designed to steer the incidence of the latter, according to a law depending on the incidence of the aircraft.

Abstract: Suspension mast for a turbine engine. According to the inventions the tilting rear fairing (6) of said mast (4) supports at least one aerodynamic element (14) that generates vortices.