The invention relates to a guide vane intended to be mounted in a turbine engine between an inner shroud (17) and an outer shroud (16), comprising a longitudinal straightening body (41) for an air flow extending between a first end (42) intended to be positioned at the inner shroud (17) and a second end (44) intended to be positioned at the outer shroud (16), the longitudinal straightening body having an aerodynamic profile defined by a leading edge (41a) and a trailing edge (41b) in the flow direction of the air flow, and by a camber line (41c) extending from the leading edge (41a) to the trailing edge (41b). It further comprises a first attachment heel (43) and a second attachment heel (45) positioned in the continuation of the longitudinal body (41) at the first end (42) and the second end (44) respectively, the first (43) and second (45) attachment heels being planar elements arranged parallel with respect to one another, each attachment heel (43; 45) being arranged at a distance from the leading edge (41a) and from the trailing edge (41b).