Patent ID: 6491260
Filing Date: 2002-12-10
Classification: B64C,Y02T

Abstract:
In an aircraft including a fuselage, a wing, and control surfaces selected from the group consisting of a high-lift flap, a slat, a spoiler, an aileron, an elevator, and a rudder,an improvement for reducing aerodynamically generated noise of air flowing over said aircraft, wherein: said improvement comprises a vortex generator arranged on a lateral end of said high-lift flap, said high-lift flap extends in a flap length direction along said wing and has an outboard end facing away from said fuselage and an inboard end facing toward said fuselage, said lateral end is said outboard end or said inboard end, said lateral end includes a profile side surface bounded between an upper side edge and a lower side edge of said high-lift flap, and said vortex generator is arranged on said profile side surface between said upper side edge and said lower side edge, and extends along at least a portion of a chord length of said high-lift flap.