A boundary layer propulsor (100) comprises a rotor (110) and a plurality of first aerofoil blades (120). The rotor has an axis of rotation (112). The plurality of first aerofoil blades extends radially from the rotor and is arranged in a circumferential array around the axis of rotation. Each of the first aerofoil blades has, in a radially outward sequence, a radially proximal portion (130), a middle portion (140), and a radially distal portion (150). The radially proximal portion has a first cambered cross-section (132), the middle portion has a second uncambered cross-section (142), and the radially distal portion has a third cambered cross-section (152). The first cambered cross-section is cambered in an opposite sense to the third cambered cross-section.


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    Title :

    PASSIVE BOUNDARY LAYER PROPULSOR


    Additional title:

    PASSIVER GRENZSCHICHT-PROPELLER
    PROPULSEUR PASSIF DE COUCHE LIMITE


    Contributors:

    Publication date :

    2021-04-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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