A wing and propeller design may reduce the power required to propel an aircraft (400) in flight. This may be achieved by reducing downwash and trailing vortices that occur naturally on the aircraft's wings. A reduction in downwash and trailing vortices may in turn reduce the overall drag on the aircraft. In one embodiment, an aircraft includes a number of propellers (410, 420, ..., 450, 460) N prop , wherein each propeller comprises a diameter d prop , has a propeller efficiency · prop , and is configured to absorb power p prop to rotate at a rate RPM to generate thrust for a flight speed V of the aircraft. The aircraft may further include a total power p total absorbed by the propellers that is approximately p prop × N prop , a wing having a circulation distribution, wherein the wing comprises a wingspan B, a drag D that is approximately equal to p total × · prop / V. For V and B , the circulation distribution, d prop , and RPM substantially minimizes D.


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    Titel :

    WING AND PROPELLER DESIGN FOR AIRCRAFT


    Weitere Titelangaben:

    FLÜGEL- UND PROPELLERDESIGN FÜR FLUGZEUGE
    CONCEPTION D'AILE ET D'HÉLICE POUR AÉRONEF


    Beteiligte:
    LIU ZHANG (Autor:in) / TALMOR AMNON G (Autor:in) / CAO YUSONG (Autor:in)

    Erscheinungsdatum :

    2018-10-17


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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