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A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
An investigation has been made to determine the effects of taper ratio, body indentation, fixed transition, and afterbody shape on the transonic aerodynamic characteristics of a 45 degree sweptback wing-body combination having an aspect ratio of 4. The results were obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.15, angles of attack from 0 to 12 degrees, and Reynolds numbers varying from 1,800,000 to 2,000,000 based on the mean aerodynamic chord of the wings.
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.