Wind Tunnel Measurements of the Mean Flow in the Turbulent Boundary Layer and Wake in the Region of the Trailing Edge of a Swept Wing at Subsonic Speeds

摘要

Measurements have been made of the distributions of local Mach number, flow direction and static pressure coefficient through the wake and boundary layers of a wing of constant chord (0.61 m normal to the leading edge) and the RAE 101 section at sweep angles of 20 and 28 degrees. The model spanned the 1.8 m (6 ft) dimension of the wind tunnel working section and was set at incidences in the range of + or - 1.88 degrees. Tests were made at free stream Mach numbers in the range 0.43 to 0.76 and Reynolds of 7 to 11 x 10 to the 6th power. The technique of measurement, using calibrated miniature three-hole yawmeters, is described and the experimental results are compared with an integral boundary-layer calculation method. Some comparisons are also made with previous tests at zero sweepback. (Author)