Supercritical aerofoils

Claim 1

A supercritical aerofoil having a leading edge, an upper and a lower surface and a trailing edge and wherein the leading edge is circular with a radius of 2% to 4% chord, the upper surface has a forward transition zone extending from said leading edge to about 20% of the distance along the chord and wherein the upper surface curvature radius increases rapidly from said leading edge radius to one from about 3 to about 5 times the chord, a constant radius zone extending from said forward transition zone for about 0.5 to 0.8 of the chord length and wherein the radius is substantially constant at 3 to 5 times the chord, and a rear zone extending to the trailing edge and wherein the curvature decreases rearwardly; the lower surface has a forward zone extending from the leading edge to a point not less than about 40% and not more than about 55% of the chord the radius of curvature whereof is at least equal to the chord but smaller than said upper surface constant radius zone radius, a curvature transition zone extending from said forward zone to between 55% and 70% of the chord, and a rearward zone extending from the transition zone to about the trailing edge and which is concave and has a mean radius of about equal to the chord, whereby a rear part of the aerofoil is effectively cambered; and said leading edge being a drooped leading edge, and the aerofoil having a thickness/chord ratio of 10% to 14%; whereby in use at supercritical speeds air passing over the upper surface is rapidly accelerated over the leading edge and forward zone to a supersonic speed and decelerated sufficiently before the trailing edge to permit the effective camber of the rear part of the aerofoil to augment the lift and without generating a shock wave sufficiently strong to cause a significant increase in drag, and in use at low speeds sufficient lift is generated for take off and landing on normal length runways.