From Introduction: "In the present report, consideration is given to certain features intended to improve the accleration-limiting characteristics of a normal-accleration control system."

Report presenting a wind-tunnel investigation at Mach number 1.96 to determine the normal forces, pitching moments, and rolling moments contributed by each wing panel of a cruciform-wing and body combination over a wide range of combined angles of pitch and roll. The wings were triangular of aspect ratio 2 and the body was an ogive-cylinder combination. Results regarding individual panels and panel combinations are provided.

Note presenting a study of the corrosion resistance of 11 nickel-base compositions to molten sodium hydroxide at 1500 and 1700 degrees Fahrenheit in order to find a container material for the caustic at these temperatures. Results are provided for the solid-solution alloys, nickel with mechanically dispersed second phase materials, and the precipitation-hardened alloy.

Note presenting a method for solving problems associated with Laplace and Poisson equations which, in general, requires considerably fewer equations than the usual methods and which gives a convergent solution by the method of successive approximations.

Report presenting an analytical expression for the lift and pitching-moment coefficients of a wing of finite thickness performing a plunging motion and rotary oscillations about some fixed angle of attack at very low frequencies in two-dimensional flow. Calculated lift and pitching-moment coefficients and design charts are presented.

Note presenting the stress-rupture properties of commercially pure nickel at 1500 degrees Fahrenheit as determined for its application as a container material for molten sodium hydroxide. Stress-rupture tests of L-nickel tubes containing sodium hydroxide were run with atmospheres of air or argon external to the tubes. Sodium hydroxide was found to have little effect on the stress-rupture strength of nickel tubes tested in argon at 1500 degrees Fahrenheit for times up to 200 hours.

Note presenting the aerodynamic characteristics of several noncircular two-dimensional cylinders with axes normal to the stream at various flow incidences for a range of Reynolds numbers as determined from low-speed wind-tunnel tests. The results indicate that these parameters have large effects on the drag and side force developed on these cylinders. Results regarding drag of two-dimensional cylinders, side force developed on two-dimensional cylinders, and directional stability and spinning characteristics of three-dimensional bodies are provided.

Report presenting a theoretical analysis of air flow in a channel in which oxygen dissociation and recombination occur. An investigation is also made of the comparative relaxation times of the oxygen dissociation-recombination reaction in relation to molecular vibrations.

Report presenting an investigation of the effect of temperature using di(2-ethylhexyl) sebacate lubricant and dry powder lubricants on rolling-contact fatigue life on AISI M-1 tool-steel balls in the rolling-contact fatigue spin rig at maximum theoretical Hertz stress levels of 650,000 and 725,000 pounds per square inch in compression.

A flight investigation was made on a large sweptback-wing bomber airplane and the results are compared with data previously obtained at low altitude (5,000 feet). The effects of wing flexibility on the wing strains were, on the average, about 20 percent larger at the higher altitude.

Report presenting an experimental investigation to determine the effects of shroud-lip radius of curvature, shroud length, and shroud diffuser angle on the static thrust characteristics of a small-scale shrouded propeller which simulated a propeller submerged in the wing of an airplane. Results regarding the effect of propeller blade angle, effect of lip radius, effect of propeller location in shroud, effect of shroud length behind the propeller plane, effect of diffuser angle, and effect of ground proximity are provided.

Note presenting an experimental investigation to study the feasibility, from considerations of lateral trim, of having all the propellers of a tilting-wing vertical-take-off-and-landing (VTOL) airplane rotate in the same direction since this is a desirable feature from practical considerations. The model was a wing with four propellers, the slipstream from which covered practically the entire span of the wing. Results regarding basic data and application of the data are provided.

Report presenting an experimental investigation of turbojet engine performance with several configurations of interacting multiple-loop controls in order to determine the ideal mode of control for optimum rotor speed and turbine-discharge temperature during thrust increase and afterburner ignition conditions.

Report presenting an investigation of the correlation of composite structural fatigue behavior, basic material, and simple-element behavior. Fatigue and static testing were made on aluminum-alloy box beams and I-beams and on elements simulating key failure locations in the two beams.

Flight tests were conducted at three conditions of damping and two atmospheric turbulence levels with fixed-reticle, gyro computing, and telescopic gunsights. Results of simulated strafing runs indicate that the gun-line dispersion could be expected to be decreased about 7 percent by increased lateral damping and to be increased about 85 percent by decreased damping and about 40 percent by rough air of the type encountered. Use of the telescopic sight indicated a 20-percent decrease in gun-line dispersion.

Note presenting a theoretical treatment for determining lift and moment on thin arrowhead or pointed-tip wings of which the delta plan form is a special case with an unswept trailing edge. Expressions have been developed for the section and total forces and moments to the third power of the reduced frequency. Sample results are given in the form of curves to show that retention of terms to the third power of the frequency gives good accuracy over a range of frequency that covers many practical flutter applications.

Report presenting six-percent-thick NACA 63-series compressor-blade sections with a loaded-leading-edge mean line investigated systematically in a two-dimensional porous-wall cascade over a range of Reynolds numbers. Blades cambered to have four different isolated-airfoil lift coefficients were tested over the usable angle-of-attack range at four different inlet-air angles and two different solidities.

Report describing the effects of an area of roughness on the velocity and turbulence measurements of an airfoil. It details the effects of the size, location, and height of the roughness on the Reynolds number. From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition."

Report presenting the low-speed yawed-rolling characteristics of two 40 x 12, 14-ply-rating, type VII aircraft under straight-yawed rolling over a range of inflation pressures and yaw angles for two vertical loadings. Static testing was performed to determine the vertical, lateral, torsional, and fore-and-aft elastic characteristics of tires. Measured lateral and torsional spring constants appeared to decrease with increasing amplitude of tire lateral distortion or twist.

Note presenting a study of the vapor-phase oxidation of methylcyclohexane in a flow system in the temperature range of 300 to 400 degrees Celsius under the conditions of 0.1 the stoichiometric amount of oxygen, a contact time of 8 seconds, and a spiral Pyrex reactor 10.5 inches long with an inside diameter of 3/32 inch. The yields of acids, aldehydes, ketones, hydrogen peroxide, organic peroxides, olefin, water, and unreacted hydrocarbon were determined in the products.

A method is presented for the calculation of lift coefficients for rectangular lifting surfaces of aspect ratios from 0.125 to 10 operating at finite depths beneath the water surface, including the zero depth or planing condition. Theoretical values are compared with experimental values obtained at various depths of submergence with lifting surfaces of aspect ratios from 0.125 to 10. The method can also be applied to hydrofoils with dihedral. Lift coefficients computed by this method are in good agreement with existing experimental data for aspect ratios from 0.125 to 10 and dihedral angles up to 10 degrees.

Report presenting overall sound-pressure levels and frequency spectra under static conditions from a modified supersonic propeller designed to operate efficiently at a high forward speed without the high noise levels associated with the supersonic propeller. The three-blade, 10-foot-diameter, 1700-rpm propeller is powered by a turbine engine and is designed to operate at a Mach number of 0.95 at 40,000 feet.

Report presenting an investigation of the effects of high temperatures incurred at hypersonic speeds using an ethylene-heated high-temperature jet.

"Calculations have been made of the initial portion of the boundary of axisymmetric free jets exhausting at large pressure ratios from a conically divergent nozzle having a jet exit Mach number of 2.5 and a semidivergence angle of 15 degrees. The results of the calculations indicate the size and shape of the jet to be expected at large pressure ratios, the effects of ratio of specific heats, and the large initial inclinations of the boundary that are likely to be encountered by hypersonic vehicles at high altitude" (p. 1).