Report presenting a flight program using the Northrop X-4 semitailless airplane to investigate the effect on the longitudinal and lateral stability and control of thickened elevons with trailing-edge thickness one-half the control-hinge-station thickness. The investigation consisted of speed runs, wind-up turns, abrupt rudder-fixed rolls, and longitudinal pulses between a range of Mach numbers.

Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.

Report presenting the longitudinal stability characteristics of the Convair XF-92A delta-wing airplane in maneuvering flight. The investigation included the determination of the characteristics of the basic airplane and the effects of two wing fence configurations on the characteristics.

Report presenting dynamic longitudinal maneuvers over a range of Mach numbers at an altitude of 30,000 feet by utilizing the XF-92A delta-wing research airplane. An analysis of the dynamic responses was made with three approaches: measured period and time to damp, analogue computer simulation of the airplane time-response characteristics, and Fourier transformation. Results regarding period, time and cycles to damp, and stability derivatives with Mach number are provided.

Report presenting flight measurements of the elevon hinge moments on the Convair XF-92A delta-wing airplane over a range of Mach numbers during longitudinal elevon pulses, aileron rolls, and wind-up turns. During wind-up turns, the hinge moments become nonlinear at about the angle of attack at which the airplane experiences a marked decrease in longitudinal stability.