Patent ID: 8100358

Claim:
A method of reducing the compressibility drag of at least one critical zone of the wing of an aircraft, the method comprising placing under said wing at least one container having a rear portion at the trailing edge of the container that tapers going away from the leading edge of the container towards the trailing edge, said rear portion being arranged at least in part upstream from the leading edge of said wing so that said container slows down the speed of the air upstream from said critical zone in order to reduce its compressibility drag, wherein the said container is given a shape that is asymmetrical so that the isobar lines surrounding the outer periphery of the container are parallel to the leading edge of said wing in said critical zone; and wherein the said container is for a generator line constituted by a straight line used for generating a surface on being rotated, said container having a plurality of generator lines in register with said rear portion, said generator lines being parallel to the leading edge of the wing in register with the zone where said container is connected to the wing.