A wing having 0° sweepback of the 0.25-chord line has been investi¬gated in conjunction with a systematic series of bodies at Mach numbers from 0.60 to 1.13 in the Langley 8-foot transonic tunnel. The wing had an aspect ratio of 4, taper ratio of 0, and 4-percent-thick, symmetrical airfoil sections parallel to the model plane of symmetry. The airfoil sections consist of circular arcs with the maximum thickness at the 0.40-chord stations. The series of bodies consisted of a body of revo-lution having a curved profile from the nose to the base, and various modifications of this basic body. The first modification had the fore-body extended forward 2 diameters, the second had a cylindrical afterbody in place of the original afterbody, and the third modification was a com¬bination of the first and second modifications resulting in a cylindrical section extending from the vicinity of the wing leading edge to the base of the model.nThe wing-body interference effects on the aerodynamic characteristics of the unswept wing were most pronounced in the transonic speed range, and the drag was most significantly affected. At low lift coefficients, the drag rise of the wing with interference was reduced approximately 20 to 30 percent by the addition of the cylindrical afterbody to the basic model at a Mach number of 1.00. The maximum lift-drag ratio for the wing when in combination with the curved afterbody was increased approx¬imately 20 percent by the substitution of the cylindrical afterbody at a Mach number of 1.00.
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