NASA technical note TN (series). D-1959. Effects of rounding corners and leading edges on windward-surface pressures of delta wing swept 65° at Mach number of 5.96 at angles of attack from 65° to 115° and angles of roll from 0° to 25° at 90° angle of attack [with list of references]; by Theodore J. Goldberg and Doris K. Blanchard.