Guide vane for a vane assembly of a turbo machine , the guide vane comprising: an aerofoil body comprising: - a forward portion (11.1), - a rear portion (11.2), and - opposite outer surfaces (11.3, 11.4), extending between the forward portion (11.1) and the rear portion (11.2), a liner configured for being fixed to the aerofoil body , the liner comprising: - a first portion (12.1) configured for being connected to the forward portion (11.1) of the aerofoil body , - a trailing edge portion (12.2) shaped with convex geometry, - a first coupling portion (12.3) extending between the first portion (12.1) and the trailing edge portion (12.2), and configured for being fixed to an outer surface (11.3, 11.4) of the aerofoil body , characterized in that , the liner further comprises - a second portion (12.4) extending from the trailing edge portion (12.2) and configured for being connected to the rear portion (11.2) of the aerofoil body , wherein when the first coupling portion (12.3) of the liner is fixed to an outer surface (11.3, 11.4) of the aerofoil body : the trailing edge portion (12.2) of the liner extends from the rear portion (11.2) of the aerofoil body , and the second portion (12.4) of the liner is connected to the rear portion (11.2) of the aerofoil body , thus forming a cavity between the rear portion (11.2) of the aerofoil body and the trailing edge portion (12.2) of the liner , wherein the trailing edge portion (12.2) of the liner forms the trailing edge of the aerodynamic profile of the guide vane , when the liner is coupled to the aerofoil body . an aerofoil body comprising: - a forward portion (11.1), - a rear portion (11.2), and - opposite outer surfaces (11.3, 11.4), extending between the forward portion (11.1) and the rear portion (11.2), - a forward portion (11.1), - a rear portion (11.2), and - opposite outer surfaces (11.3, 11.4), extending between the forward portion (11.1) and the rear portion (11.2), a liner configured for being fixed to the aerofoil body , the liner comprising: - a first portion (12.1) configured for being connected to the forward portion (11.1) of the aerofoil body , - a trailing edge portion (12.2) shaped with convex geometry, - a first coupling portion (12.3) extending between the first portion (12.1) and the trailing edge portion (12.2), and configured for being fixed to an outer surface (11.3, 11.4) of the aerofoil body , characterized in that , the liner further comprises - a second portion (12.4) extending from the trailing edge portion (12.2) and configured for being connected to the rear portion (11.2) of the aerofoil body , - a first portion (12.1) configured for being connected to the forward portion (11.1) of the aerofoil body , - a trailing edge portion (12.2) shaped with convex geometry, - a first coupling portion (12.3) extending between the first portion (12.1) and the trailing edge portion (12.2), and configured for being fixed to an outer surface (11.3, 11.4) of the aerofoil body , characterized in that , the liner further comprises - a second portion (12.4) extending from the trailing edge portion (12.2) and configured for being connected to the rear portion (11.2) of the aerofoil body , the trailing edge portion (12.2) of the liner extends from the rear portion (11.2) of the aerofoil body , and the second portion (12.4) of the liner is connected to the rear portion (11.2) of the aerofoil body , thus forming a cavity between the rear portion (11.2) of the aerofoil body and the trailing edge portion (12.2) of the liner , <EOS>