A rotor blade for a high-pressure compressor rotor of a gas turbine engine , the rotor blade configured to be mounted to a support structure for rotation about an axis of rotation , the rotor blade comprising: a mount configured to be attached to the support structure ; and a blade that extends from the mount along a radial axis and that terminates at a blade tip , the blade including a leading edge and a trailing edge , the leading edge having a hub point located at an intersection of the leading edge and a platform of the mount , a tip point located at an intersection of the leading edge and the blade tip , and an intermediate point disposed between the hub point and the tip point relative to the radial axis ; wherein the leading edge includes an indent segment that extends between the tip point and the intermediate point , the indent segment including a nadir point ; wherein an imaginary leading edge profile extends continuously from the intermediate point to the tip point in a radial direction; wherein the indent segment is indented from the imaginary leading edge profile in a transverse direction relative to the radial axis ; wherein the leading edge has a leading edge radial length measured along the radial axis from the hub point to the tip point ; wherein the indent segment has an indent radial length measured along the radial axis from the tip point to the intermediate point ; wherein the indent segment has an indent depth measured from the nadir point to the imaginary leading edge profile along a mean axis of the blade , the mean axis extending between the leading edge and the trailing edge at a constant radial distance from the axis of rotation ; wherein a first ratio of the indent radial length to the leading edge radial length is at most 0.5; and wherein a second ratio of the indent depth to the indent radial length is at least 0.05. a mount configured to be attached to the support structure ; and a blade that extends from the mount along a radial axis and that terminates at a blade tip , the blade including a leading edge and a trailing edge , the leading edge having a hub point located at an intersection of the leading edge and a platform of the mount , a tip point located at an intersection of the leading edge and the blade tip , and an intermediate point disposed between the hub point and the tip point relative to the radial axis ; wherein the leading edge includes an indent segment that extends between the tip point and the intermediate point , the indent segment including a nadir point ; wherein an imaginary leading edge profile extends continuously from the intermediate point to the tip point in a radial direction; wherein the indent segment is indented from the imaginary leading edge profile in a transverse direction relative to the radial axis ; wherein the leading edge has a leading edge radial length measured along the radial axis from the hub point to the tip point ; wherein the indent segment has an indent radial length measured along the radial axis from the tip point to the intermediate point ; wherein the indent segment has an indent depth measured from the nadir point to the imaginary leading edge profile along a mean axis of the blade , the mean axis extending between the leading edge and the trailing edge at a constant radial distance from the axis of rotation ; wherein a first ratio of the indent radial length to the leading edge radial length is at most 0.5; and wherein a second ratio of the indent depth to the indent radial length is at least 0.05. <EOS>