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.