Wind tunnel tests were carried out to determine the effect on the longitudinal aerodynamic characteristics of a two-dimensional aerofoil fitted with descrete forward-facing wedges (base to aerofoil chord ratio 0.24 and 0.39) at the leading edge and on the upper surface of the aerofoil. The forward-facing wedges were conceived as a means of delaying stall and enhancing lift at high incidence. Thus these may be useful in low speed flight (approach and landing) where they would be extended from the clean wing surface along with the trailing edge flaps. Tests were conducted at Mach numbers 0.2/0.3, over an incidence range of -10 to +20 degrees. Corresponding chord Reynolds numbers were 0.57 and 0.84 million (compared to an inflight value of 2.5 million for a wing of chord 1.25 metres and airspeed of 60 knots). The results at M=0.2 are more extensive than those at M=0.3.