A method of optimizing the profile of a composite material blade for a rotor wheel of a turbine engine, the blade comprising an airfoil constituted by a plurality of blade sections stacked in a radial direction of the wheel, a root for mounting on a disk of the wheel and extended by a tang, and an inner platform situated between the tang and the airfoil, the root being connected to the tang by a neck, the method being characterized in that it comprises the following steps: a step of compensating the blade airfoil, which step consists in subdividing the airfoil into slices, each defined between a bottom section and a top section, and for each airfoil slice and for a predetermined speed of rotation of the wheel disk, calculating the centrifugal force (F C) to which the slice is subjected, calculating the moment of the aerodynamic force acting on the bottom section of the slice, and calculating shift values to be applied to the center of gravity of the slice in tangential and longitudinal directions in order to cancel the moment of the aerodynamic force acting on the bottom section of said slice, the shift values (δ X, δ Y) for application to the center of gravity of an airfoil slice being given by the following formulas: δ X = M Y − faero / F C δ Y = M X − faero / F C with: M X-faero being the component of the moment of the aerodynamic force acting on the bottom section of the slice in the longitudinal direction; and M Y-faero being the component of the moment of the aerodynamic force acting on the bottom section of the slice in the tangential direction, and a step of compensating the blade tang, consisting in calculating the centrifugal force (F' C) to which a portion of the blade situated above the neck is subjected, which portion is constituted by the airfoil, by the inner platform, and by the tang, calculating the moment of the aerodynamic force acting on a bottom section of the tang of the blade, and calculating shift values to be applied to a center of gravity of the blade tang along the tangential and longitudinal direction in order to cancel the moment of the aerodynamic force acting on the bottom section of the blade tang, the shift values (δ' X, δ' Y) for application to the center of gravity of an airfoil slice being given by the following formulas: δ ′ X = M ′ Y − faero / F ′ C δ ′ Y = M ′ X − faero / F ′ C with: M' X-faero being the component of the moment of the aerodynamic force acting on the bottom section of the blade tang in the longitudinal direction; and M' Y-faero being the component of the moment of the aerodynamic force acting on the bottom section of the blade tang in the tangential direction. a step of compensating the blade airfoil, which step consists in subdividing the airfoil into slices, each defined between a bottom section and a top section, and for each airfoil slice and for a predetermined speed of rotation of the wheel disk, calculating the centrifugal force (F C) to which the slice is subjected, calculating the moment of the aerodynamic force acting on the bottom section of the slice, and calculating shift values to be applied to the center of gravity of the slice in tangential and longitudinal directions in order to cancel the moment of the aerodynamic force acting on the bottom section of said slice, the shift values (δ X, δ Y) for application to the center of gravity of an airfoil slice being given by the following formulas: δ X = M Y − faero / F C δ Y = M X − faero / F C with: M X-faero being the component of the moment of the aerodynamic force acting on the bottom section of the slice in the longitudinal direction; and M Y-faero being the component of the moment of the aerodynamic force acting on the bottom section of the slice in the tangential direction, and a step of compensating the blade tang, consisting in calculating the centrifugal force (F' C) to which a portion of the blade situated above the neck is subjected, which portion is constituted by the airfoil, by the inner platform, and by the tang, calculating the moment of the aerodynamic force acting on a bottom section of the tang of the blade, and calculating shift values to be applied to a center of gravity of the blade tang along the tangential and longitudinal direction in order to cancel the moment of the aerodynamic force acting on the bottom section of the blade tang, the shift values (δ' X, δ' Y) for application to the center of gravity of an airfoil slice being given by the following formulas: δ ′ X = M ′ Y − faero / F ′ C δ ′ Y = M ′ X − faero / F ′ C with: M' X-faero being the component of the moment of the aerodynamic force acting on the bottom section of the blade tang in the longitudinal direction; and M' Y-faero being the component of the moment of the aerodynamic force acting on the bottom section of the blade tang in the tangential direction.