CMC airfoil with thin trailing edge

An airfoil as may be used in a gas turbine engine includes a ceramic matrix composite (CMC) element that extends to define a leading edge portion and chord portion of the airfoil, and a separately formed but conjoined trailing edge element that defines a desirably thin trailing edge of the airfoil without the need for using an excessively small bend radius for reinforcing fibers in the CMC element. The trailing edge element may include a plurality of interlock elements that extend through the trailing edge attachment wall of the CMC element and provide mechanical attachment there between. Alternatively, the trailing edge element may be adhesively bonded or sinter bonded to the CMC element. A cooling air insert may be disposed within a cooling air cavity of the CMC element and may include cooling tubes that extend into the trailing edge element to deliver cooling air there through.