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A wind-tunnel investigation has been made through a speed range from a Mach number of approximately 0.90 to determine the lateral-control characteristics of a 2-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoiler on a semispan-wing model with aspect ratio of 3.06 having 51.3 degree sweepback of the wing leading edge. In addition, the aerodynamic characteristics of the plain wing were determined through the speed range.
An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
An investigation was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.96 to determine the characteristics of a wing trailing-edge jet control on a 1/16-scale model of the Douglas D-558-II research airplane. The control was operated with ram air obtained from wing-tip inlets. The characteristics of ailerons and trailing-edge spoilers were also obtained for comparison with the jet control.