Turbomachine blade having a sweep law with high flutter margin

A turbomachine rotor blade comprising

• a plurality of blade sections stacked along an axis Z between a blade root and a blade tip defining between them the height of the blade,
• each section including
• a leading edge,
• a trailing edge,
• a pressure side, and
• a suction side,
• each section presenting
• a height between 0% corresponding to the blade root and 100% corresponding to the blade tip,
• a chord defined by a length of a chord line connecting the leading edge and the trailing edge,
• a camber line formed of all points located at equal distance from the suction side and the pressure side,
• a maximum camber defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of the camber line,
• a ratio between the maximum camber and the chord,
• wherein
• a ratio of a section at mid-height of the blade is comprised between 25% and 40% of a ratio of a section at the blade root,
• a ratio of a section at the blade tip is comprised between 25% and 40% of the ratio of the section at the blade root.