| 摘要 |
The invention relates to aviation technology and can be used for improving the lift-drag ratio of helicopters and aeroplanes, including classically configured large airliners, and amphibious craft, aerodynamic ground-effect craft and hovercraft, possibly by modernization thereon. The technical problem addressed is that of reducing flight drag, possibly as a result of modernizing the helicopter, aeroplane, aerodynamic ground-effect craft or hovercraft. The technical result is achieved by reducing the contact area of the external surface of the tail part of the fuselage with a rapid air flow, for which the above-mentioned contact area is reduced by increasing the area of an opening in the tail part of the fuselage.; In order to increase the lifting force without increasing the pressure resistance in an aerodynamic duct, the base is upwardly convex, for example is curved upwards following the shape of a convex side of an aerodynamic profile. The upper opening in the fuselage skin for the aerodynamic duct can be arranged in a space along the middle part of the rudder fin and is divided, for example in half, to the right and left along the rudder fin. The aerodynamic duct is continuous and can be open. An opening which is aligned with the leading upper edge of the aerodynamic duct has a larger area than a rear opening therein, which is aligned with the end of the fuselage, possibly in the form of and by means of a cut section in the end of the fuselage. |
