Nozzle of a turbomachine provided with chevrons with a non-axisymmetric inner face

A cover 2 for a nozzle of longitudinal axis L-L, the internal wall 3 of the cover having a section with a predetermined abscissa XO on the L-L axis defining, on the wall, a neck line 71, said cover having, downstream from abscissa, indentations 9 in the trailing edge 5 of the cover 2 delimiting chevrons 10 distributed in the circumferential direction, in which, on the cover, from the abscissa: - the internal wall (3, figure 1) moves away radially towards the outside of the upstream tangent (70, figure 3), to the top 11 of an indentation , - the outer wall (4, figure 1) of the cover moves towards the upstream tangent to the top of an indentation, and - the internal wall moves away radially towards the inside of the upstream tangent (79, figure 3), to the tip 13 of a chevron, wherein the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the abscissa.