An Investigation Of The Lift Drag And Static Stability Characteristics Of A Triangular Wing Airplane Configuration At Mach Numbers From 300 To 628

Lift, drag, and static-stability characteristics of a triangular-wing airplane were determined at Mach numbers from 3.00 to 6.28, angles of attack up to 13 degrees at zero sideslip angle, and angles of sideslip up to 8 degrees at zero angle of attack. The test configuration consisted of a triangular wing mounted on a cylinder afterbody with a fineness-ratio-3 tangent-ogive nose, and a single vertical-tail surface with a trapezoidal plan form. This configuration closely approximates a class of current operational transonic aircraft. Data were also obtained with the basic configuration modified by the addition of a conical flare to the afterbody.