Patent ID: 6513761
Filing Date: 2003-02-04
Classification: B64C,Y02T

Abstract:
An apparatus for reducing trailing flap vortices (11, 12) of an aircraft generated by wing components including lift producing trailing edge landing flaps (7, 8) of aircraft wings (3, 4) having a given span width, said landing flaps each having an outer flap end (7A, 8A) relative to a central longitudinal aircraft axis (CA) at which outer flap end said trailing flap vortices are produced when said landing flaps are extended, said apparatus comprising at least one controllable auxiliary flap operable as a counter vortex generator (9, 10) secured to at least one wing in a mounting area (MA) of a fixed wing portion of at least one of said aircraft wings (3, 4) and relative to at least one of said trailing edge landing flaps (7, 8) for generating a controlled counter vortex for counteracting a respective trailing vortex of said trailing vortices (11, 12) downstream of a respective wing, wherein said mounting area (MA) of said at least one controllable auxiliary flap operable as a vortex generator (9, 16) has a length in either wing direction away from a wing chord (EL) passing through said outer end (7A, 8A) of a respective landing flap of said landing flaps (7, 8), said length of said mounting area (MA) corresponding to 10% of one half said given span width of said aircraft, whereby said at least one auxiliary flap is so positioned that said controlled counter vortex is injected into said respective trailing vortex to vibrate said respective trailing vortex thereby dissipating said respective trailing vortex at least partially.