An Experimental Technique for Boundary Layer Research at High Reynolds Numbers

摘要

The pressure distribution over the upper surface of a special smooth wing on a "Hart" aeroplane was modified by means of a duct to represent that over the front part of the wing of a larger and faster aeroplane. The pressure minimum occurred at a distance of 0.6 of the chord from the leading edge and the local velocity there was 1.6 times the flight speed. Transition took place just in front of the pressure minimum.