Wind-tunnel investigation at high subsonic speeds of a spoiler-slot deflector combination on an NACA 65A006 wing with quarter-chord line swept back 32.6 degrees

An investigation was made in the Langley high-speed 7by 10-foot tunnel through a Mach number range from 0.4 to 0.91to determine the lateral control characteristics of a wing-fuselage combination with the wing qurter-chord line swept back 32.60, an aspect ratio of 4, a taper .ratio of 0.6,and an NACA 6~AO06 section.One wing panel was equipped with a 50-percent-semispan inboard spoiler-slot-deflector combination located between the 55and 70-percent-chord lines.. * As was previously found at low speed, the loss in rolling-moment effectiveness of an unvented spoiler at high wing angles of attack is materially reduced by the incorporation of a slot and deflector at Mach numbers up to 0.91.The optimum ratio of deflector to spoiler projec- tion for best results varied with angle of attack, but a ratio of threefourths to one gave appreciable roQing-moment effectiveness through the angle-of-attack range from O" to 20".