Patent ID: 9284046
Filing Date: 2016-03-15
CPC Classification: B64C,B64D,Y02T

Claim Text:
1. An aircraft with improved aerodynamic performances, for maintaining direction stability and optimal aerodynamic behaviour with a medium-high incidence; said aircraft comprising a fuselage to which wings are associated, at least one air intake and a nose with a tapered section, and at least one engine; wherein said aircraft comprises a control device of the vortex of a leading edge extension of the wing leading edge root extension, in which the ratio between the surface of one leading edge extension and a height of a corresponding control device is 2.35 m with a variable tolerance in a range from 100% and −50% of the ratio, comprising between 1.175 m and 4.70 m, said control device of the vortex generated by the edge, cooperates with a tail, obtained by coupling of a vertical tail with the wings whose leading edges penetrate trailing edges of each wing; an equipment comprising at least one dissipating device of incident radar waves which is removably applied on at least one hot portion of the aircraft; the at least one hot portion of the aircraft comprising: a piloting cabin or cockpit having at least one transparent portion; a fuselage frame; a plurality of leading edges of components, the components comprising wings, tail veils and air intakes of the at least one engine; at least one engine face; wherein to reduce radar marking from the at least one engine face, the equipment comprises at least one grid having an inner structure with a plurality of apertures, and a support structure having a plurality of rings securing said grid to the aircraft; each of the apertures comprises an internal surface coated with radar absorbing material adapted to absorb electromagnetic waves at high frequency; said grid is adapted to permit entry of air flow towards the at least one engine and reduce radar visibility of the at least one engine face of the aircraft.