A film-cooled component for a gas turbine engine, comprising: a first surface of the component located at a gas path of a gas turbine engine; a second surface of the component defining an internal component passage; and a cooling airflow passage extending from the second surface to the first surface to convey a cooling airflow from the internal component passage and emit the cooling airflow at the first surface, wherein the cooling airflow passage has a passage inlet at the second surface and a passage outlet at the first surface, the passage outlet having an area that is greater than the area of the passage inlet, wherein a lateral direction is perpendicular to the local gas flow direction and a streamwise direction is parallel to the local gas flow direction; characterised in that: the cooling airflow passage is defined along a major axis by an outboard surface radius and an inboard surface radius laterally offset from the outboard surface radius wherein the inboard surface radius is greater than the outboard surface radius; the outboard surface radius is defined in a first plane at a first angle ranging from 15 degrees to 90 degrees to the gas flow direction; the inboard surface radius is defined in a second plane oriented angularly offset from both the first plane and the streamwise direction; and the cooling airflow passage diffuses the cooling airflow in at least two directions relative to a local gas flow direction in the gas path. a first surface of the component located at a gas path of a gas turbine engine; a second surface of the component defining an internal component passage; and a cooling airflow passage extending from the second surface to the first surface to convey a cooling airflow from the internal component passage and emit the cooling airflow at the first surface, wherein the cooling airflow passage has a passage inlet at the second surface and a passage outlet at the first surface, the passage outlet having an area that is greater than the area of the passage inlet, wherein a lateral direction is perpendicular to the local gas flow direction and a streamwise direction is parallel to the local gas flow direction; characterised in that: the cooling airflow passage is defined along a major axis by an outboard surface radius and an inboard surface radius laterally offset from the outboard surface radius wherein the inboard surface radius is greater than the outboard surface radius; the outboard surface radius is defined in a first plane at a first angle ranging from 15 degrees to 90 degrees to the gas flow direction; the inboard surface radius is defined in a second plane oriented angularly offset from both the first plane and the streamwise direction; and the cooling airflow passage diffuses the cooling airflow in at least two directions relative to a local gas flow direction in the gas path. the cooling airflow passage is defined along a major axis by an outboard surface radius and an inboard surface radius laterally offset from the outboard surface radius wherein the inboard surface radius is greater than the outboard surface radius; the outboard surface radius is defined in a first plane at a first angle ranging from 15 degrees to 90 degrees to the gas flow direction; the inboard surface radius is defined in a second plane oriented angularly offset from both the first plane and the streamwise direction; and the cooling airflow passage diffuses the cooling airflow in at least two directions relative to a local gas flow direction in the gas path.