Paul G. Fournier
Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at a Mach number of 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65A-series airfoil sections. Other configurations included bodies modified by two types of indentation and two other wings, one wing without camber but with 4 degrees linear twist (washout) and a second wing with both camber and twist.
An Adobe Acrobat (PDF) file of the entire report: