Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.


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    Title :

    LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT


    Additional title:

    FÜR MIT ÜBERSCHALL- UND HOHER UNTERSCHALLGESCHWINDIGKEIT FLIEGENDE FLUGZEUGE OPTIMIERTER LAMINARFLUSSFLÜGEL
    AILE À ÉCOULEMENT LAMINAIRE OPTIMISÉE POUR AÉRONEF À VOL TRANSSONIQUE ET SUPERSONIQUE


    Contributors:

    Publication date :

    2021-01-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT

    TRACY RICHARD R / STURDZA PETER / CHASE JAMES D | European Patent Office | 2015

    Free access

    LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT

    TRACY RICHARD R / STURDZA PETER / CHASE JAMES D | European Patent Office | 2015

    Free access

    LAMINAR FLOW WING OPTIMIZED FOR SUPERSONIC AND HIGH SUBSONIC CRUISE AIRCRAFT

    TRACY RICHARD / STURDZA PETER / CHASE JAMES | European Patent Office | 2018

    Free access