A helicopter (100) comprises a fuselage (102), a main rotor (106) coupled to the fuselage (102) and that in operation rotates in a first rotational direction with respect to the fuselage (102), an engine (110) carried by the fuselage (102) and drivingly coupled to rotate the main rotor (106) in the first rotational direction with respect to the fuselage (102), a tail boom (112) that extends rearwardly of the fuselage (102), the tail boom (112) having an approaching side and a retreating side (132), the approaching side being a side of the tail boom (112) that the main rotor (106) approaches when rotating in the first rotational direction, the retreating side (132) being a side of the tail boom (112) that the main rotor (106) retreats from when rotating in the first rotational direction, the retreating side (132) opposite the approaching side across a width of the tail boom (112), the approaching side of the tail boom (112) having a varying radius of curvature about a centerline, the retreating side (132) of the tail boom (112) has a varying radius of curvature about the centerline of the tail boom (112), and the radius of curvature over a portion of the tail boom (112) is infinite, and the tail boom (112) having an upper half, a lower a half and a horizontal plane (248) that extends between the upper half and the lower half of the tail boom (112), a first strake that extends outwardly from the approaching side of the tail boom (112), the first strake (130) positioned below the horizontal plane of the tail boom (112) at a position that is from approximately 5 degrees to 15 degrees above a location at which flow separation would otherwise occur on the approaching side below the horizontal plane in the absence of the first strake, and at least one vortex generator (136) that extends outwardly from the retreating side (132) of the tail boom (112), the at least one vortex generator (136) positioned below the horizontal plane of the tail boom (112) at a position that is from approximately 5 degrees to 15 degrees above a location at which flow separation would otherwise occur on the retreating side (132) below the horizontal plane in absence of the at least one vortex generator (136).


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    Title :

    HELICOPTER WITH ANTI-TORQUE SYSTEM, RELATED KIT AND METHODS


    Additional title:

    HUBSCHRAUBER MIT GEGENDREHMOMENTSYSTEM, ZUGEHÖRIGES KIT UND VERFAHREN
    HÉLICOPTÈRE À SYSTÈME ANTI-COUPLE, KIT ET PROCÉDÉS ASSOCIÉS


    Contributors:

    Publication date :

    2021-09-01


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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