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.