Experimental investigations have been made of the now characteristics on wings of moderate sweepback. This note presents the results of the experimental investigation into the pressure distribution over a swept back wing, having an aspect ratio 4. 5 and sweep back angle 40° at quarter chord. A half model technique has been used. The wing section was R. A. E. 101 (symmetrical) with 6% maximum thickness and zero camber. Measurements of chordwise pressure distributions at a number of spanwise sections were made in the incidence range 2 - 32°. The experiments were performed at Reynolds numbers of 0. 9 x 10(6) and 2 x 10(6) (based on geometric mean chord). From these measurements, lift, drag and pitching moment characteristics of the wing were calculated.