Abstract: An aerofoil component for a high-pressure or intermediate-pressure turbine of a multi-spool gas turbine engine having an aerofoil member which spans a working gas annulus of the gas turbine engine. The aerofoil member has pressure side and suction side aerofoil surfaces which each extend from a leading to a trailing edge such that transverse cross sections through the aerofoil member provide respective aerofoil sections. The spacing between the leading and trailing edges on the midspan aerofoil section defines a midspan axial chord length. The aerofoil member are arranged in a circumferential row around the annulus with plural, equally spaced, identical aerofoil members whereby the circumferential spacing of the aerofoil members at the trailing edges of their midspan aerofoil sections defines a midspan pitch of the aerofoil member. At midspan: the value of S/Cx is in the range from 1.4 to 1.6; and the uncovered turning angle is 16° or more.