The design of two-dimensional aerofoils with mixed boundary conditions

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Abstract
A method is given of designing two-dimensional symmetrical aerofoils in subsonic compressible flow when the boundary conditions are mixed. The aerofoil surface is divided into three parts such that the shape is prescribed in the first and third and the pressure distribution is specified in the second. The method has the advantage over the usual method of aerofoil design (pressure distribution given over the whole aerofoil surface) of giving the designer direct control of the nose shape and the trailing edge angle.

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