INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF A COMBINATION JET-FLAP AND DEFLECTED-SLIPSTREAMnCONFIGURATION AT ZERO AND LOW FORWARD SPEEDS

摘要

An investigation of the aerodynamic characteristics of a semispan wing equipped with a 38.5-percent-chord sliding flap partially immersed in the slipstream of two propellers has been conducted in the 17-foot test section of the Langley 300-MPH 7- by 10-foot tunnel. The wing had an aspect ratio of 7.0, taper ratio 1.0, and an NACA 63A412 airfoil sec¬tion. The propellers were one wing chord in diameter. A jet of air -was ejected over the knee of the flap through a momentum-coefficient range from zero to about 1.0.nThe data are presented without analysis;however, a few significant results have been noted. Large losses in lift were encountered at low forward speeds for values obtained within ground proximity compared with values obtained out of ground proximity.