A method for improving a blade in an end zone of the blade, spanwise along the blade, and such an improved blade and a rotor comprising the improved blades. The leading edge of the aerodynamic profiles situated in the end zone is shifted from the upper surface half-profile towards the lower surface half-profile, then the leading edge sections of the two half-profiles are modified in order to connect the leading edge to the intermediate sections of the two half-profiles. Next, the blade is manufactured according to the modified aerodynamic profiles. Consequently, the negative camber of the aerodynamic profiles of the blade is thus increased, helping improve the aerodynamic performances of the blade during hovering flight.
METHODE D'AMELIORATION DU COMPORTEMENT AERODYNAMIQUE DE PALES D'UN GIRAVION EN VOL STATIONNAIRE PAR UN DEPLACEMENT DU BORD D'ATTAQUE DES PROFILS AERODYNAMIQUES DE CES PALES
METHOD FOR IMPROVING THE AERODYNAMIC PERFORMANCE OF BLADES OF A HOVERING ROTORCRAFT BY MOVEMENT OF THE LEADING EDGE OF THE AERODYNAMIC PROFILES OF THESE BLADES
VERFAHREN ZUR VERBESSERUNG DES AERODYNAMISCHEN VERHALTENS DER BLÄTTER EINES DREHFLÜGELFLUGZEUGS IM SCHWEBEFLUG DURCH VERSCHIEBUNG DER VORDERKANTE DER AERODYNAMISCHEN PROFILE DIESER BLÄTTER
2023-02-15
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
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