Abstract: A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A hybrid type rotorcraft having a main rotor, at least two propulsion elements each mounted on respective half-wings arranged symmetrically on either side of an anteroposterior midplane XOZ, a horizontal stabilizer arranged in a rear zone of the rotorcraft on either side of the anteroposterior midplane XOZ, and two fins arranged respectively on either side of the anteroposterior midplane XOZ, each of the two fins comprising a respective left/right bottom fin airfoil arranged below the horizontal stabilizer and a respective left/right top fin airfoil arranged above the horizontal stabilizer.

Abstract: A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.

Abstract: A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack.

Abstract: A hybrid type rotorcraft having a main rotor, at least two propulsion elements each mounted on respective half-wings arranged symmetrically on either side of an anteroposterior midplane XOZ, a horizontal stabilizer arranged in a rear zone of the rotorcraft on either side of the anteroposterior midplane XOZ, and two fins arranged respectively on either side of the anteroposterior midplane XOZ, each of the two fins comprising a respective left/right bottom fin airfoil arranged below the horizontal stabilizer and a respective left/right top fin airfoil arranged above the horizontal stabilizer.

Abstract: A dome for a rotor comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face towards a top face above the bottom face. The dome includes at least one slot extending between the periphery and the axis of rotation in elevation, each slot passing right through a thickness of the cap by extending in elevation from the bottom face to the top face.

Abstract: A dome for a rotor of a rotorcraft, the dome comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face for facing a hub of the rotor towards a top face above the bottom face. At least one of the top and bottom faces is an undulating face that undulates at least in azimuth between the periphery and the axis of rotation in elevation, by including in azimuth along at least one internal circle a succession of bulges and of recesses.

Abstract: A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.

Abstract: A dome for a rotor comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face towards a top face above the bottom face. The dome includes at least one slot extending between the periphery and the axis of rotation in elevation, each slot passing right through a thickness of the cap by extending in elevation from the bottom face to the top face.

Abstract: A dome for a rotor of a rotorcraft, the dome comprising a cap extending radially from an axis of rotation in elevation towards a periphery and in azimuth over 360 degrees, the cap extending in thickness from a bottom face for facing a hub of the rotor towards a top face above the bottom face. At least one of the top and bottom faces is an undulating face that undulates at least in azimuth between the periphery and the axis of rotation in elevation, by including in azimuth along at least one internal circle a succession of bulges and of recesses.