LARGE-SCALE WIND-TUNNEL TESTS OF AN AIRPLANE MODEL WITH AN UNSWEPT TILT WING OF ASPECT RATIO 5.5, AND WITH VARIOUS STALL CONTROL DEVICES

摘要

Results are presented of the effects of slats, flaps, wing-fuselage ramp fairing, and propeller rotation on the flow separation, buffet, and descent characteristics of a tilt-wing deflected-slipstream VTOL model. The results indicated that wing stall and resulting buffet in descending flight could be delayed, approximately 15 knots by a slat, BLC nose flap, or increased trailing-edge flap effectiveness.