Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.

An investigation has been made to obtain the effects of a 20-percent-semispan all-movable wing-tip control (which was deflected -5 to -10 degrees) on the longitudinal stability characteristics of a twisted and cambered 60 degrees sweptback-wing-indented-body configuration equipped with fences at angles of attack which generally varied from 0 to 16 degrees and over the Mach number range of 0.80 to 1.13. The Reynolds number based on the mean aerodynamic chord varied from 2,010,000 to 2,220,000.

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.43 for a 45 degree sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.