Turbomachine blade having a maximum thickness law with high flutter margin

A turbomachine rotor blade comprising

• a plurality of sections stacked along an axis Z between a blade root and a blade tip, each section including:
• a leading edge,
• a trailing edge,
• a pressure side, and
• a suction side,
• each section having:
• a height extending from 0% corresponding to the blade root and 100% corresponding to the blade tip,
• a chord defined by a length of a portion of a line connecting the leading edge and the trailing edge,
• a maximum thickness defined by a maximum distance between the suction side and the pressure side, and
• a ratio of the maximum thickness to the chord for each of the plurality of sections,
• wherein:
• the ratio of a section at 30% of the height of the blade is between 20% and 42% of the ratio of a section at the blade root,
• the ratio of a section at 70% of the height of the blade is between 10% and 30% of the ratio of the section at the blade root,
• the ratio of a section at 90% of the height of the blade is between 10% and 30% of the ratio of the section at the blade root, and
• the ratio of a section at the blade tip is comprised between 3% and 21% of the ratio of the section at the blade root,
• wherein the ratio of each section depending on the height of the section is defined by a curve comprising a plurality of linear segments, the ratio defined by the plurality of linear segments decreasing as the height of a given section increases or remaining constant as the height of a given section increases, and
• wherein the plurality of line segments of the curve comprises a first line segment extending from the blade to root of 30% of the height of the blade, a second line segment extending from 30% to 70% of the height of the blade, a third line segment extending from 70% to 90% of the height of the blade, and a fourth line segment extending from 90% of the height of the blade to the blade tip.