Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.

Report presenting an investigation of the transonic flutter characteristics of models of an all-movable horizontal tail of a fighter airplane. Results regarding simulated airplane tests, the effects of pitch stiffness with rearward pitch axis, and the effect of pitch-axis location are provided.

Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.

Report presenting a free-flight investigation of the zero-lift control effectiveness of a steady-flow jet-spoiler roll control on a cruciform 80 degree delta-wing missile over a range of Mach numbers. Measurements were made of the rolling-moment, damping-in-roll derivative, drag, and pressures at the inlet and on the wing near the jet exit. Results indicated that the wing and jet combination magnified the thrust force of the isolated jet alone by factors of 11 at subsonic speeds to 3 at supersonic speeds.

Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.