AN AIRCRAFT ROTOR BLADE OF SHAPE ADAPTED FOR ACOUSTIC IMPROVEMENT DURING APPROACH FLIGHTS AND FOR IMPROVING PERFORMANCE IN HOVERING FLIGHT AND IN FORWARD FLIGHT

摘要

The present invention relates to a blade (1) of a rotor (11) for a rotary wing (10). The blades 1 are designed to increase the aerodynamic performance of the blades 1 in both the forward flight and the stop flight in order to reduce the noise generated during the second approach flight, 1 and the sweep, chord, and twist of the airfoil profile 15 of the sections of the airfoil profile. The blade (1) is doubly tapered and provides three sweeps. The twist relationship is substantially constant over the first portion of the blade and decreases over the remainder of the blade in a linear or non-linear manner. The appropriate change in the gradient of the twist of the blade 1 makes it possible to improve the aerodynamic performance of the blade in forward and hover flights.