A turboengine blading member (1) is disclosed. The blading member comprises at least one airfoil (2) and at least one platform (31) provided at at least one of a base and a tip of the airfoil (2). The airfoil (2) comprising a profile body (23), a leading edge (21) provided at a first side of the profile body (23), and a trailing edge section (24) extending from a second side of the profile body (23) and opposite the leading edge (21). The profile body (23) is connected to the at least one platform (31). The trailing edge section (24) cantilevers from the profile body (23) and is provided without connection to the platform (31).