Abstract: "The ductility of Type 310 stainless steel T-joints brazed with GE-62 brazing alloy was measured at room temperatures 1200, 1650, and 1800 F. The measure of ductility was taken as the plastic axial strain required to crack braze fillets in T-section tensile specimens. At elevated temperatures, the ductility of as-brazed joints approximated that of the stainless steel, but at room temperature the brazed joints had only one-tenth the ductility of the base metal. Annealing for 16 hr at 1800 F in air was found to triple the room-temperature ductility of the brazed joint."

Abstract: A device is proposed for confining charged particles to a localized region of space by means of the alternating electric field of a resonant cavity. The motion of single electrons in the field is stable. The limitations to particle density and temperature are discussed, and found to be too severe to allow the device to serve as a reactor, although it might be a useful laboratory tool.

"The relation of Whitcomb's "area rule" to the linear formulas for wave drag at lightly supersonic speeds is discussed. By adopting an approximate relation between the source strength and the geometry of a wing-body combination, the wave-drag theory is expressed in terms involving the areas intercepted by oblique planes or Mach planes. The resulting formulas are checked by comparison with the drag measurements obtained in wind-tunnel experiments and in experiments with falling models in free air. Finally, a theory for determining wing-body shapes of minimum drag at supersonic Mach numbers is discussed and some preliminary experiments are reported" (p. 757).

Report presenting the results of an investigation of cross-sectional-area distribution, nacelle configuration, and landing-gear-fairing configuration on the minimum drag characteristics of a model of a four-engine bomber airplane with a low-aspect-ratio triangular wing. The lateral stability characteristics are also included.

Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.

Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.

Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.

Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.

Report presenting an adhesive, FPL-710, which produces higher strength at temperatures up to 600 degrees Fahrenheit than previously obtained and possesses good resistance to aging at high temperatures. It also has acceptable resistance to creep and immersion in various organic solvents. Results regarding its strength properties, heating and aging resistances, and variables affecting bond strength are provided.

Report presenting an investigation to determine the effects of camber on the aerodynamic characteristics of a series of rectangular wings with various aspect ratios and thickness-to-chord ratios using the transonic-bump method. Testing occurred over a range of Mach and Reynolds numbers. Lift, drag, and pitching-moment characteristics are presented for wings of 5 aspect ratios, NACA 63A2XX and 63A4XX sections, and 5 thickness-to-chord ratios.

The rate of uranium sorption by a strong-base anion-exchange resin (Dovex 21K) from a uranyl sulfate solution (U 0.005 M, H2SO4 0.02M, SO4 0.2 M) was studied using a stirred vessel technique and measuring the U235 gamma radiation on each bead. Resin initially in the chloride form and the sulfate for was studied.

The following report is divided into two parts, both parts center around the effects of radiation on skin tissue. Part one focuses on superficial radiation, or Beta rays, while part two is on penetrating radiation, or neutrons and gamma rays.

Report discussing progress made by the National Research Corporation regarding preparation of ductile zirconium during the month of May, 1949.

Abstract: "This is a compilation of the material in several reports on the extraction of uranium from aqueous solutions with dibutyl carbitol. Data is presented concerning the optimum conditions for the extraction of the uranium and elimination of impurities."

Abstract: "This is a compilation of the data on uranium peroxide precipitations appearing in several reports. The solubility product is measured. The effect of many individual ions on the hydrogen peroxide decomposition rate and the complexing of uranium is demonstrated. Studies on plant and other highly contaminated solutions are not included."

Compilation of carbon monoxide band positions, molecular constants, energy levels, potential energy curves, and other molecular properties derived from the spectrum.

Report issued by the Oak Ridge National Laboratory displaying a single chart showing measurements of the gamma-ray, fast-neutron, and thermal-neutron dose rates.

A report on paper chromatography in synthetic organic chemistry.

"An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6" (p. 1).

Report presenting an investigation of the flow properties of a constant-outer-wall annual diffuser in combination with a tailpipe in order to come up with a configuration suitable for turbojet afterburners. Information about axial inlet flow and whirling inlet flow is provided. During testing, a vena contrata region formed downstream from the center body terminal and rendered the first 1/2 diameter of the tailpipe ineffective.

"The compression plane is intended for operation on or close to the surface of the water, and has a hull with a concave bottom which forms the upper surface of a tunnel into which air is forced under pressure to support part of the load. The results of the tests made in Langley tank no. 1 include values of the horizontal forces, trimming moment, and static pressure in the tunnel for a wide range of loads and speeds and two power conditions, and are presented in the form of curves against speed with load as a parameter. The results are scaled up to 10 times the model size for three conditions at which the model is self-propelled at a steady speed" (p. 1).

From Summary: "A method is presented for calculating the lift and centers of pressure of wing-body and wing-body-tail combinations at subsonic, transonic, and supersonic speeds. A set of design charts and a computing table are presented which reduce the computations to routine operations. Comparison between the estimated and experimental characteristics for a number of wing-body and wing-body-tail combinations shows correlation to within + or - 10 percent on lift and to within about + or - 0.02 of the body length on center of pressure."

"An investigation was made of the take-off characteristics of a 1/10-scale dynamic model of the Convair XF2Y-1 airplane. This airplane is a water-based, jet-propelled, delta-wing fighter incorporating a hydro-ski landing gear. Tests were made with the original configuration, with the beaching wheels removed, and with the wheels installed and fairings added in front of the wheels" (p. 1).

The intuitive concept that a sector shaped centrifuge cell is free from convection is criticized. Not only is a form of convection present for a single sedimenting species, but a more insidious type occurs in a mixture having an appreciable Johnston-Ogston effect. Rather than striving for convection-free sedimentation, the proposal is to utilize if possible an apparently harmless type of convection occurring in a very thin annulus in order to avoid the convection extending between boundaries in a mixture. The requirement that the concentrations be independent of time meets this condition and yields a hyperbolic cell, which is approximated by a sector cell placed in the rotor backwards. Simultaneously, area measurements and calculations involving the Johnston-Ogston anomaly are simplified because of the time independence.