A turbine section for a gas turbine engine comprising: a pair of adjacent turbine airfoils , each airfoil 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 having a first airfoil and a second airfoil ; and an endwall extending between the second side of the first airfoil and the first side of the second airfoil , the endwall 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 (P) 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 (P) 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 (P) 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 , each airfoil 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 having a first airfoil and a second airfoil ; and an endwall extending between the second side of the first airfoil and the first side of the second airfoil , the endwall 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 (P) 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 (P) 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 (P) 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 (P) 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 (P) 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 (P) 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 . <EOS>