Report presenting a theoretical investigation to determine the static and dynamic characteristics of a control-surface actuator and missile combination, with primary consideration given to the minimization of the effects of Mach number and altitude.The results indicate that the type of actuator studied in combination with a missile might replace a gain-adjusted acceleration control system. Results regarding the control-system static characteristics, control-system dynamic characteristics, comparison of torposervo and position-servo actuation, and some suggestions for further research are provided.

From Introduction: "The use of automatic controls to reduce the tendency for rolling divergence has been investigated in references 2 and 3. These studies have considered the effect of artificial changes in certain stability derivatives on the rolling divergence, and have shown that increased damping in pitch may be quite effective in reducing the divergent tendency. In the present report, a different type of automatic control is investigated."

Report presenting force-test data showing the effects of change in leading-edge radius on the low-speed longitudinal stability of a 6-percent-thick 45 degree sweptback wing of aspect ratio 3 for several ranges of Mach and Reynolds numbers. The results indicated that as the airfoil sections were thinned at the nose, separation effects occurred at lower values of lift coefficient.

Report presenting flight measurements of the horizontal-tail loads on the Douglas X-3 research airplane during wind-up turns, pull-ups, and stabilizer pulses over a range of altitudes and Mach numbers.