Abstract:
The tests described in this report were made in the 1-ft Circular Tunnel at the National Physical Laboratory at a Nach number of about 1.4. The main object was to determine the lift obtainable from wings of very short span and in particular to see whether tile lift curve departed much from a straight line at incidences up to about 12 deg., it being already known that the lift curve for a two-dimensional aerofoil was sensibly straight up to 20 deg. or so of incidence. Unfortunately it was not possible to measure the drag load, so that only normal force and pitching moment values are available.
