Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowable center-of-gravity travel are provided.

Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.

Report presenting an investigation to determine the effect of leading-edge chord-extensions on high-lift pitching moment and performance characteristics at subsonic and transonic speeds. Three models with the same wings were used. Results regarding low-speed development and high-speed characteristics are provided.

Report presenting aerodynamic characteristics in steady roll on a complete model and its component parts. The model consisted of a wing and horizontal tail with a 45 degree sweepback at the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding rolling moment due to rolling, yawing moment due to rolling, and lateral force due to rolling are provided.

Report presenting an investigation in the transonic tunnel to determine the aerodynamic characteristics of a wing-fuselage combination with a 45 degree sweptback wing with NACA 65A006 airfoil sections, an aspect ratio of 4, taper ratio of 0.6, and incorporating outboard leading-edge slats. Results lift characteristics, influence of slats on wing pressure distribution, drag characteristics, lift-drag ratio characteristics, and pitching-moment characteristics are provided.

Report presenting a wind-tunnel investigation to study the effects of operating propellers on the low-speed longitudinal characteristics of a four-engine tractor airplane configuration. The coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are provided. Tests were conducted at a range of Mach and Reynolds numbers.

From Summary: "The present investigation was conducted to determine, from low-speed tests in the Langley stability tunnel, the static and rotary derivatives of a 1/9-scale model of the Republic F-91 airplane and various of its components (including the effects of wing incidence) and to determine the accuracy with which the period and damping of the lateral oscillation of the airplane could be calculated by using these experimentally between flight and calculated period and damping of the lateral oscillation were made for Mach numbers from 0.4 to 0.9 at an altitude of 20,000 feet for 0 degrees wing incidence and several other wing incidences. Some comparisons were made of the static and rotary derivatives of the model and derivatives estimated by available procedures."

"An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/23-scale model of the Lockheed XFV-1 airplane to determine the effects of control setting and movement upon the erect-spin and recovery characteristics for a range of airplane loading conditions. A windmilling propeller was simulated on the model for some of the tests. The investigation included determination of the size of tail parachute required for emergency recovery from demonstration spins" (p. 1).

The hydrodynamic characteristics of a preliminary design of the Martin XP6M-1 flying boat have been determined. Longitudinal stability during take-off and landing, resistance of the complete model, and behavior during taxiing and landing in rough water are presented.