Aerofoil recambering

A method of recambering an aerofoil section (48) wherein the aerofoil section (48) is one of a spanwise array forming an aerofoil (36);

• the aerofoil section (48) having a leading edge (40), a trailing edge (42), a suction surface (46), a pressure surface (44), and a camber line (50) equidistant from the suction and pressure surfaces (46, 44) and having an upstream end (49) and a downstream end (51);
• the method comprising steps to:
• a) determine a position (58) on one of the pressure surface (44) and the suction surface (46) that intersects with a passage shock (56) between adjacent aerofoils (36);
• b) project the shock position (60) onto the camber line (50);
• c) define a shock region (62) encompassing the shock position (60) and extending in a chordal direction towards the leading and trailing edges (40, 42);
• d) recalculate the position of the camber line (50) in an upstream region (65) between the shock region (62) and the upstream end (49) of the camber line (50) to match calculated pressure loading between the suction and pressure surfaces (46, 44) to a first target pressure loading distribution (66);
• e) project the camber line (50) across the shock region (62) to match a geometric criterion;
• and
• f) recalculate the position of the camber line (50) in a downstream region between the shock region (62) and the downstream end (51) of the camber line (50) to match calculated pressure loading between the suction and pressure surfaces (46, 44) to a second target pressure loading distribution (70).