METHOD OF DETERMINING AN INITIAL ATTACK EDGE CIRCLE OF AERODYNAMIC PROFILES OF A BLADE AND IMPROVEMENT OF THE BLADE IN ORDER TO INCREASE ITS NEGATIVE INCIDENCE OF STALL

摘要

The present invention relates to a method for determining an initial leading edge circle of the aerodynamic profiles of a blade and improving a blade as well as such an improved blade and an advancing propeller comprising said improved blades. . The radius of an initial leading edge circle (15,25) of each aerodynamic profile (10) of said blade is determined and then increased and its leading edge (5) is moved by half a profile of intrados (21) towards an extrados half-profile (11), thus modifying the aerodynamic profile (10) of each cross section of said blade and the camber of each aerodynamic profile (10). Consequently, a negative incidence of stalling of said blade is increased, in absolute value, thus making it possible to increase the aerodynamic performance of said blade under a negative incidence compared to an unmodified blade, without significant degradation of its aerodynamic performance under a positive impact.