Patent ID: 7520470
Filing Date: 2009-04-21
Classification: B64C,Y02T

Abstract:
1. Configuration of an aircraft ( 10 ) with improved aerodynamic performance, so as to maintain direction stability at mid/high angles of attack, said aircraft ( 10 ) having a fuselage ( 12 ) fitted with wings ( 18 , 20 ) and leading edge extensions each leading edge extension (“LEX”) having an area at least one air intake ( 46 ) and a fuselage forebody ( 52 ) with a tapering section, said aircraft ( 10 ) including a LEX vortex control device ( 72 ) shaped such as to make symmetrical the bursting of the vortex generated by a said LEX at mid/high angles of attack, wherein the ratio of the LEX area over the corresponding LEX vortex control device height is equal to 2.35m with a tolerance range varying from about 200% to about 50% of said ratio, said LEX vortex control device cooperating with staggered tails comprising a single vertical fin ( 38 ) and at least one horizontal stabilizer ( 44 ), obtained by coupling the vertical fin ( 38 ) to the wing ( 18 , 20 ), wherein the leading edges ( 36 ) of the vertical fin ( 38 ) overlap the tailing edges ( 70 ) of each wing ( 18 , 20 ), in order to maintain lateral-directional stability.