A method of recambering an aerofoil section. A position on one of the surfaces that intersects with a passage shock between adjacent aerofoils is determined and then projected as a shock position onto the camber line. A shock region encompassing the shock position and extending in a chordal direction towards the leading and trailing edges is defined. The camber line is recalculated in an upstream region using semi-inverse design. The camber line is extrapolated across the shock region to match a geometric criterion. The camber line is recalculated in a downstream region using semi-inverse design.