A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface; a second component having an first surface oriented towards the second surface of the first component, a second surface opposite the first surface of the second component, and a cooling hole extending from the second surface of second component to the first surface of second component, wherein the second surface of the first component and the first surface of the second component define a cooling channel therebetween, and wherein the second component has a variable thickness along a first length of the second component, the variable thickness being configured to adjust a distance between the first surface of the second component and the second surface of the first component throughout the first length such that a Mach number of a cross airflow within the cooling channel is adjusted.