Abstract: A method for modeling an offset portion of a blade of a non-ducted propeller is provided. The method includes: parametrizing a C1-class curve representing a deformation of the blade characterizing the offset, according to a position along a section at a given height in the blade, the curve intersecting consecutively through a first bend control point, a central control point, and a second bend control point, the first and second bend control points defining the extent of the blade section, the parametrization being implemented according to a first deformation parameter defining the abscissa of the central control point, a second parameter of deformation defining the ordinate of the second bend point, and a third deformation parameter defining the angle of the tangent to the curve at the second bend control point; optimizing one of the deformation parameters; and plotting the values of the optimized parameters on an interface.

Abstract: (EN) The present invention relates to a method for modeling at least one portion of a blade (2) of a non-ducted propeller (1), wherein the blade portion (2) is offset (3).

Abstract: The invention relates to an aircraft turboprop engine having two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of the terminal edge.

Abstract: The invention relates to an aircraft turboprop engine comprising two unducted propellers, coaxial about a rotation axis (LL), respectively upstream (12) and downstream (14?), each propeller comprising an annular row of blades, the blades of the downstream propeller (14?) each having a truncated head and each comprising a leading edge (20?) and a trailing edge (22?), the radially external ends (A2, B1) of which are distant from each other and are connected by a terminal edge (21?), characterised in that the terminal edge (21?) of each blade of the downstream propeller (14?) has, at at least two points, tangents in a meridian plane having different slopes, the upstream end (A) of the terminal edge defining a maximum radial dimension (R2) of the blade and its downstream end (B1) defining a minimum radial dimension (R3) of said terminal edge.