Static Stability And Control Of Canard Configurations At Mach Numbers From 070 To 222 Longitudinal Characteristics Of A Triangular Wing And Unswept Canard

The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.15 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.