An airfoil is configured to reduce lift pressures in relaxing spans adjacent to the airfoil's tip to avoid vortex formation. The relaxing span is configured to enable negative air angles of attack on thin airfoils to reduce pressure differences. The configuration enables more-efficient long-chord blunt edges/tips on low aspect ratio airfoils having utility in a plurality of applications including aircraft wings, turbine blades, and ductless fans.
Airfoil Superstructure
14.03.2024
Patent
Elektronische Ressource
Englisch