A WIND-TUNNEL INVESTIGATION OF THE WAKE NEAR THE TRAILING EDGE OF A DEFLECTED EXTERNALLY BLOWN FLAP

摘要

An investigation was made to determine the behavior of the flow near the trailing edge (that is, in the near wake) of a deflected externally blown flap. The model tested was a general research model of a swept-wing, jet-powered STOL transport with externally blown flaps. The model was tested with four engine simulators mounted on pylons under the wing. Tests were conducted in the Langley V/STOL tunnel over an angle-of-attack range of 0° to 16° and a thrust-coefficient range from 0 to approximately 4 at a Reynolds number of 0.461 x 106 based on the wing reference chord.nThe results of this investigation are presented primarily as plots of the individual velocity vectors obtained from the wake survey. These data are used to extend an earlier analysis to isolate the effects of the engine thrust on the behavior of the flow at the flap trailing edge. Results of a comparison with a jet-flap theory are also shown.