An airfoil array for a gas turbine engine comprising: a plurality of airfoils spaced circumferentially apart from each other about an engine center axis, each airfoil being associated with a platform, the plurality of airfoils including at least a first airfoil type supported on a first platform and a second airfoil type that is different than the first airfoil type and is supported on a second platform adjacent the first platform, wherein the first platform and the second platform have different platform geometries; an endwall extending circumferentially about the engine center axis, the endwall being defined by the adjacent platforms (68a, 68b), and wherein each pair of adjacent platforms (68a, 68b) are separated from each other by a gap; and an endwall contour shape defined to extend from a first edge location on one side of the gap to a second edge location on an opposite side of the gap, the first and second edge locations (110, 112) respectively corresponding to edges (104, 106) of a common endwall contour region; wherein the endwall contour shape is defined by a first portion extending from the first edge location to the gap and a second portion extending from the opposite side of the gap to the second edge location; wherein within the common endwall contour region, the endwall contour shape is identical for all adjacent platforms (68a, 68b) regardless of the overall platform geometry, such that the first and second portions (114, 116) of the endwall contour shape of the first platform adjacent to the second platform terminate at locations (84a, 86a) that directly face each other across the gap; and wherein outside of the common endwall contour region, in the remaining areas (102a, 102b) between the respective airfoils (62a, 62b) and edges (104, 106) of the common endwall contour region, endwall contouring varies to smoothly blend back into the optimal design shape for the respective airfoil. a plurality of airfoils spaced circumferentially apart from each other about an engine center axis, each airfoil being associated with a platform, the plurality of airfoils including at least a first airfoil type supported on a first platform and a second airfoil type that is different than the first airfoil type and is supported on a second platform adjacent the first platform, wherein the first platform and the second platform have different platform geometries; an endwall extending circumferentially about the engine center axis, the endwall being defined by the adjacent platforms (68a, 68b), and wherein each pair of adjacent platforms (68a, 68b) are separated from each other by a gap; and an endwall contour shape defined to extend from a first edge location on one side of the gap to a second edge location on an opposite side of the gap, the first and second edge locations (110, 112) respectively corresponding to edges (104, 106) of a common endwall contour region; wherein the endwall contour shape is defined by a first portion extending from the first edge location to the gap and a second portion extending from the opposite side of the gap to the second edge location; wherein within the common endwall contour region, the endwall contour shape is identical for all adjacent platforms (68a, 68b) regardless of the overall platform geometry, such that the first and second portions (114, 116) of the endwall contour shape of the first platform adjacent to the second platform terminate at locations (84a, 86a) that directly face each other across the gap; and wherein outside of the common endwall contour region, in the remaining areas (102a, 102b) between the respective airfoils (62a, 62b) and edges (104, 106) of the common endwall contour region, endwall contouring varies to smoothly blend back into the optimal design shape for the respective airfoil.