US 12,214,864 B2
Aircraft portion with a reduced drag
Xavier Bernard, Saint Cloud (FR); Zdenek Johan, Saint Cloud (FR); and Aurélien Merlet, Saint Cloud (FR)
Assigned to DASSAULT AVIATION, Paris (FR)
Filed by DASSAULT AVIATION, Paris (FR)
Filed on Sep. 27, 2023, as Appl. No. 18/373,276.
Claims priority of application No. 22 09883 (FR), filed on Sep. 29, 2022.
Prior Publication US 2024/0109648 A1, Apr. 4, 2024
Int. Cl. B64C 23/06 (2006.01); B64C 1/26 (2006.01)
CPC B64C 23/06 (2013.01) [B64C 1/26 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An aircraft portion of an aircraft comprising:
a fuselage extending along a longitudinal direction and having a median longitudinal plane;
an airfoil formed by at least one pair of wings arranged on either sides of the fuselage along a transverse direction orthogonal to the median longitudinal plane;
an airfoil-fuselage junction fairing at an interface between the airfoil and the fuselage, the airfoil-fuselage junction fairing having an outer surface comprising two lateral portions each covering a wing root of a respective one of the wings, and a lower portion connecting the two lateral portions to each other, extending under the fuselage, an air flow around the airfoil-fuselage junction fairing during a movement of the aircraft generating at least two induced vortices induced on both sides, respectively, of the median longitudinal plane; and
at least two vortex generating devices extending from the lower portion of the outer surface of the airfoil-fuselage junction fairing on both sides, respectively of the median longitudinal plane.