Patent ID: 6260809
Filing Date: 2001-07-17
Classification: B64C

Abstract:
An aircraft rotor (10) having a plurality of rotary-wing blades (12) for rotation in a direction about a common rotor axis (14), each rotary-wing blade (12) including a tip portion (16) radially outward from the rotor axis (14), the improvement wherein the tip portion (16) of each of said rotary-wing blades (12) further includes a respective ovate loop tip (20), each ovate loop tip (20) being at the radially outermost portion of the rotary-wing blade (12) and having an ovate geometry transverse to the direction of blade rotation and being substantially symmetric with respect to a plane defined substantially by the chord of the tip portion (16) of the rotary-wing blade (12), thereby to reduce the intensity of blade tip vortices.