The invention is related to an airfoil (1a) for a rotor blade (1) of a rotary wing aircraft, said airfoil (1a) having a predetermined maximum thickness to chord ratio and comprising, between a leading edge (3a) and a trailing edge (3b), an extrados (4b) and an intrados (4a), said intrados (4a) being defined by predetermined intrados coordinate value pairs and said extrados (4b) being defined by predetermined extrados coordinate value pairs, wherein a maximum error of each one of said predetermined intrados coordinate value pairs and said predetermined extrados coordinate value pairs amounts to ±3%.
AIRFOILS FOR ROTOR BLADES OF ROTARY WING AIRCRAFTS
SCHAUFELN FÜR ROTORBLÄTTER VON DREHFLÜGLERLUFTFAHRZEUGEN
PROFILS AÉRODYNAMIQUES POUR PALES DE ROTORS POUR DES AÉRONEFS À VOILURE TOURNANTE
2017-09-13
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |