Report discussing the stability and control characteristics and drag of a canard or tail-first configuration explored using the free-fall method. Information about the basic flight characteristics, experimental coefficients, zero-lift drag configurations, and longitudinal stability and trim characteristics is provided.

Report presenting measurements of the longitudinal stability and control characteristics of a canard airplane configuration using the wing-flow method. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model with control settings between several different degrees. The experimental data are presented in summarized or abridged form and calculated trim curves are presented for various flight loading conditions.

Report presenting a theoretical analysis of a supersonic canard missile configuration to show the means that might be used to improve its dynamic performance characteristics. The analysis was conducted by using the best available estimates of aerodynamic and airframe parameters. Results regarding missile longitudinal performance, selection of rate factor, angle of attack and normal acceleration, frequency response, pole plots, and tip control are provided.