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.


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    Title :

    Airfoil Superstructure


    Contributors:

    Publication date :

    2024-03-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64C AEROPLANES , Flugzeuge



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