Large-scale wind-tunnel tests of an airplane model with an unswept tilt wing of aspect ratio of 5.5, and with various stall control devices

Results are presented of t h e e f f e c t s of slats, f l a p s , wing-fuselage ramp f a i r i n g , and p r o p e l l e r r o t a t i o n on t h e flow separation, b u f f e t , and descent c h a r a c t e r i s t i c s of a tilt-wing deflected-slipstream VTOL model.The r e s u l t s indicated t h a t wing s t a l l and r e s u l t i n g b u f f e t i n descending f l i g h t could be delayed approximately 15 knots by a s l a t , BLC nose f l a p , o r increased t r a i l i n gedge f l a p effectiveness.