Investigation of spoiler-slot-deflector ailerons and other spoiler ailerons on a 45 degree sweptback-wing--fuselage combination at Mach numbers from 0.60 to 1.03

A n investigation was conducted i n t h e Langley 16-foot transonic tunn e l t o determine the characteristics of several flap-type spoiler ailerons, lower-surface deflector ailerons, and spoiler-slot-deflector ailerons.These controls were located in the vicinity of the 7O"percent w i n g chord l i n e and extended outboard t o 87 percent of the wing semispan.The flaptype spoilers were t e s t e d a t only one projection.The wing of the wingbody combination used i n t h e s e t e s t s had 450 sweepback, an aspect ratio of 4.0, a t a p e r r a t i o of 0.60, and NACA 6 5 ~0 0 6 a i r f o i l s e c t i o n s p a r a l l e l t o the plane of symmetry.Six-component force and moment data were obtained a t Mach numbers from 0.60 t o 1.03 (Reynolds nurnbers from 5.05 x lo6 t o 6.0 x 10 6 ) f o r an angle-of -attack range from Oo t o approximately 20°.The r e s u l t s show that, although the flap-type spoiler ailerons had more rolling-moment effectiveness than the spoiler-slot-deflector controls a t l o w angles of attack, these ailerons became ineffective a t high angles; whereas the l a t t e r control maintained appreciable effectiveness through the angle-of-attack range a t a l l t e s t Mach numbers.Removal of small inboard segments of the flap-type spoiler had l i t t l e e f f e c t on the rollingmoment characteristics.L i t t l e o r no improvement i n t h e rolling-moment characteristics of a spoiler-slot-deflector control were obtained by e i t h e r increasing the deflector chord length or by adding leading-edge chordextensions t o t h e outboard sections of the wing.The reversal of rollingimoment effectiveness a t moderate angles of attack shown by deflector cont r o l s was not prevented either by decreasing deflector projection o r by adding a gap between the deflector and the w i n g .