Further, the airfoil contours that would be produced by a conventional leading edge flap or slat system would be dependent upon the fixed wing leading edge shape, and therefore, the resulting airfoil contour would be less than ideal. If they were structurally capable of use at high speeds they would have the disadvantage of producing an excessive amount of drag. Because of the high airloads and structural forces imposed, they are not practical at high speed flight. Leading edge flap or slat devices have been employed for changing the camber of an airfoil, but these devices are primarily employed during low speed flight, such as take-off and landing. The kinematic linkage mechanism is slaved to rotating means of the rib member, for torsionally twisting the outermost edge of the airfoil section, upper surface portion, the precise amount of rotation so as to flexuously bend the upper surface and thereby contour it to conform to an aerodynamically predetermined curvilinear plot that will produce the desired camber and the change in the lift characteristics of the airfoil surface. A hinged rib member, through a kinematic linkage mechanism associated between itself and the structure at the outermost edge of the airfoil section, bends and torsionally twists the airfoil edge forming structure about a relative spanwise axis. The cambering apparatus comprises an upper surface flexible skin panel which is supported along its inner edge by a wing spar assembly and along its outermost edge, by an airfoil edge forming structure.
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