Aerodynamic characteristics at Mach 0.60 to 4.63 of two cruciform missile models, one having trapezoidal wings with canard controls and the other having delta wings with tail controls

摘要

Investigations have been conducted in an 8-foot transonic pressure tunnel, the 4-foot supersonic pressure tunnel, and the Unitary Plan wind tunnel at Mach numbers from 0.60 to 4.63 to determine the aerodynamic characteristics of two missile configurations which utilized a common body. One configuration had trapezoidal wings and canard controls; the other configuration had delta wings and aft tail controls. In addition, two forebody shapes were tested, one conical and the other a blunted ogive. The results indicate that both configurations have a high degree of maneuvering capability, with the tail controls providing higher trimmed lift values up to a Mach number of 2.86 and the canard controls providing higher values above a Mach number of 2.86. The canard controls providing higher values above a Mach number of 2.86. The canard configuration has the larger aerodynamic-center variation between subsonic and supersonic Mach numbers, and the conical forebody generally has slightly higher drag than the blunted ogive.