An air vehicle fuselage (2) adapted for transonic operation is disclosed. The fuselage has a body (6) and a close-out (8). A lower surface of the body (6) has a first waterline value at the transition (14) to the close-out. A lower surface of the close-out (8) has a waterline value that varies along a fore-aft direction of the fuselage and is equal to the first waterline value at the transition station (14) and connects to an upper surface of the close-out at an aft end of the close-out. The fuselage (2) also has a drag-reduction blivet (20), i.e. a local deformation deviating from a conventional smooth profile, disposed on the lower surface of the close-out. The blivet includes a first region (A) wherein the lower surface drops to a point comprising a third waterline value that is below the first waterline value and a first inward radius and then rises over a second region (B) disposed aft of the first region wherein a second radius that is a minimum radius of the lower surface within the second region is greater than the first radius.
Aircraft fuselage drag reduction blivet
Flugzeugrumpfausbauchung zur Luftwiderstandsreduzierung
Renflement de fuselage d'aéronef pour réduire la traînée
2017-05-03
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
Reduction of Fuselage Form Drag by Vortex Flows
AIAA | 1999
|ROTORCRAFT FUSELAGE DRAG REDUCTION USING COMBUSTION POWERED ACTUATORS
British Library Conference Proceedings | 2011
|