Patent ID: 8186616
Filing Date: 2012-05-29
Classification: B64C,Y02T

Abstract:
1. A hybrid aerofoil configured for a wing of an aircraft, the hybrid aerofoil being profiled for transonic and subsonic flight conditions of the wing and having a respective transonic design point and a respective subsonic design point, said aerofoil comprising a leading edge, a trailing edge and a chord dimension therebetween, and comprising: an upstream portion having an upstream profile characteristic of subsonic aerofoils including a relatively rounded leading edge, wherein said upstream profile is configured for reducing a magnitude of a suction peak and retarding development of trailing edge flow separation at said subsonic design point including subsonic high lift coefficient flight conditions as compared with that obtained with a reference transonic aerofoil having a relatively sharp leading edge, and comprising a camber greater than 1% of said chord dimension at a position less than about 30% along said chord from said leading edge at said transonic and subsonic flight conditions, and a camber greater than 2% at a position greater than 60% along said chord from said leading edge; and a downstream portion including a mid-portion having a mid-portion profile characteristic of transonic aerofoils, wherein said mid-portion profile is shaped for delaying formation of shockwaves and minimizing wave drag at said transonic design point including transonic Mach numbers, wherein said camber has a non-negative camber distribution with respect to the chord, wherein said camber distribution comprises maxima at a position greater than 60% of said chord from said leading edge, and wherein said upstream portion comprises a leading edge radius of greater than 2.5% of said chord dimension at said subsonic design point and at said transonic design point.