Lateral-control investigation at transonic speeds of retractable spoiler and plug-type spoiler-slot ailerons on a tapered 60 degree sweptback wing of aspect ratio 2 : transonic-bump method

g a t i o n u t i l i z i n g the transonic-bump technique through a Mach number of 0.619 t o 1.167 has been made i n the Langley high-speed 7by 10-foot tunnel t o determine t h e l a t e r a l c o n t r o l c h a r a c t e r i s t i c s of r e t r a c t a b l e s p o i l e r and plug-type s p o i l e r -s l o t a i l e r o n s .The wfng had a sweepback of 60° a t the quarter-chord line, an aspect r a t i o of 2, a taper ratio of 0.6, and an NACA 6 5 ~0 0 6 a i r f o i l s e c t i o n p a r a l l e l to t h e f r e e stream.The plug-type spoiler-slot aileron w a s more e f f e c t i v e In producing roll than the retractable spoiler aileron throughout the Mach number, projection, and angle-of-attack ranges investigated.The plug-type spoilerslot aileron exhibited a large increase i n aileron effectiveness at the higher angles of attack over the effectiveness at zero angle of a t t a c k up t o a Mach number of 0.959.The use of downgoing spoilers on one win@; i n conJunction wfth upgohg s p o i l e r s on the o t h e r wing increased the aileron effectiveness at low angles of a t t a c k b u t was i n e f f e c t i v e o r reduced the aileron effectiveness at high angles of attack.The yawing moments were generally favorable for both the retractable spoiler and plug-type spoiler-slot ailerons. .-.. URCMSSfFfED