FULL-SCALE INVESTIGATION OF BOUNDARY-LAYER CONTROL BY SUCTION THROUGH LEADING-EDGE SLOTS ON A WING-FUSELAGE CONFIGURATION HAVING 47.5° LEADING-EDGE SWEEP WITH AND WITHOUT FLAPS

摘要

The maximum—lift coefficient of the plain wing without suction was 1.03 and the application of suction at a high flow rate increased the maximum lift to 1.20. The wing in the sealed and faired condition was longitudinally unstable at stall, but with suction applied along the out board 73—percent span at the most forward leading—edge slot (1/2—percent chord] the instability near maximum lift was eliminated.nApplying suction at a high flow rate along the outboard 50-percent wing span with this slot resulted in a maximum-lift coefficient of 1.13 and longitudinal stability throughout the lift range.nThe installation of split flaps resulted in maximum-lift values similar to the unflapped wing with and without boundary—layer suction and was longitudinally unstable for all conditions investigated.