"Halves of cone bodies having fineness ratios of 2, 4, or 6 were tested with thin flat wings at Mach 10.03 and Reynolds numbers of 1.2X106, 1.5X106, or 1.8X106. Several wing planforms designed empirically or theoretically to match the shape of the shock wave about the body were investigated for each fineness ratio. Tests were also made with thick wings and with wings having various leading-edge shapes. The wing planforms which matched the actual shock shape provide the highest lift-drag ratios. Increasing the fineness ratio of the half-cone body increase the lift-drag ratio but decreases the lift coefficient. Effects of wing thickness and leading-edge shape were very small."--P. [i].