Abstract:
The measurements were of pressure distribution at one section of the wing and along the wing-body junction of a half model. The wing was of STAC 11 section (12 per cent thick normal to the leading edge and of roof-top upper-surface design pressure distribution). The chord Reynolds numbers of the tests were from 1.4 to 5.7 million. Results at the lowest Reynolds number are of doubtful value because of uncertainty of the boundary layer condition. At higher Reynolds number the wing pressure correlate fairly well, on a basis of conditions normal to the leading edge, with those on the same model with wing set at 60 degrees sweep, and with two-dimensional section results but small differences lead to an increase in pressure drag. The wing-body junction pressure distribution is inadequately predicted by the design method used.
