A turbine section (28, 34) for a gas turbine engine comprising: a pair of adjacent turbine airfoils (59A, 59B), each airfoil (59A, 59B) including a first side, a second side, a leading edge, a trailing edge, and an axial chord length extending between the leading edge and the trailing edge, the pair of turbine airfoils (59A, 59B) having a first airfoil and a second airfoil; and an endwall (64A, 64B) extending between the second side of the first airfoil and the first side of the second airfoil, the endwall (64A, 64B) comprising: a first feature adjacent the second side of the first airfoil between the leading edge and the trailing edge, characterized by the first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil; a second feature adjacent the first feature between the leading edge and the trailing edge, the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil; and by a third feature adjacent the second feature and first side of the second airfoil between the leading edge and the trailing edge, the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil. a pair of adjacent turbine airfoils (59A, 59B), each airfoil (59A, 59B) including a first side, a second side, a leading edge, a trailing edge, and an axial chord length extending between the leading edge and the trailing edge, the pair of turbine airfoils (59A, 59B) having a first airfoil and a second airfoil; and an endwall (64A, 64B) extending between the second side of the first airfoil and the first side of the second airfoil, the endwall (64A, 64B) comprising: a first feature adjacent the second side of the first airfoil between the leading edge and the trailing edge, characterized by the first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil; a second feature adjacent the first feature between the leading edge and the trailing edge, the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil; and by a third feature adjacent the second feature and first side of the second airfoil between the leading edge and the trailing edge, the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil. a first feature adjacent the second side of the first airfoil between the leading edge and the trailing edge, characterized by the first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil; a second feature adjacent the first feature between the leading edge and the trailing edge, the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil; and by a third feature adjacent the second feature and first side of the second airfoil between the leading edge and the trailing edge, the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil.