The bibliography provided investigates the following sources: Chemical Abstracts 1947-1950., Metallurgical Abstracts Vols. 1-18., ASM Review of Metals Literature Vols. 1-6., J. Institute of Metals Vols. 78-80 (No. 7)., Physics Abstracts 1937-1950.

"The split reactor of the Critical Experiment is analyzed, using a single-energy group-diffusion approximation. A further approximation is introduced in that the two halves of the reactor are treated as a parallelopipeds rather than the half-cylinders. The reactivity of the reactor is obtained as a function of the separation of the two halves, both for the 'standard' uranium concentration and for various greater concentrations."

Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.

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.

Results of tests to determine the aerodynamic forces and moments on bodies of revolution at angles of attack from 0 degrees to 25 degrees are presented and compared with theory. Cones and ogives of fineness ratios 3 to 7 and two blunt-nosed body shapes with fineness ratios 3 and 5 were tested at Mach numbers from 2.75 to 5.00. Reynolds numbers were from 0.5 million to 6.4 million, depending on Mach number and body fineness ratio.

From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."

From Introduction: "A survey of some of the advantages and problems associated with transpiration cooling of gas-turbine engines is given in reference 1, and its is shown therein that high pressure gradients around the periphery of gas-turbine blades require that the blade wall permeability be varied around the blade periphery in order for uniform cooling to be obtained over the entire blade surface. This fact is verified in experimental investigations of transpiration-cooled turbine blades mounted in a static cascade (references 2 and 3) where it is shown that although transpiration cooling results in extremely effective cooling in the midchord region of the blade, there are very large variations in the chordwise temperature distribution because of improper permeability variation."

Report presenting a study of the supersonic longitudinal stability and control characteristics of a canard missile configuration using flight tests and wind-tunnel tests at a range of Mach numbers and Reynolds numbers. Good correlation was noted for the two techniques for slopes of lift and moment coefficients against angle of attack and for aerodynamic-center location.

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.

Report presenting an investigation utilizing the transonic-bump technique through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral control characteristics of retractable spoiler and plug-type spoiler-slot ailerons. The wing had a sweepback of 60 degrees at the quarter-chord line, an aspect ratio of 2, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The plug-type spoiler-slot aileron was found to be more effective in producing roll than the retractable spoiler aileron through the entire range of values tested.

Report presenting free-fall testing of the airplane configuration described in the title to evaluate certain new testing techniques for near sonic speeds. Results regarding the drag measurements and pressure data are provided. The data obtained from this test is also compared to free-fall tests in the high-speed tunnel and for a rocket-powered free-flight model, and the results show generally satisfactory agreement.

Report presenting an experimental two-dimensional investigation of the mechanism of the flow and losses involved in the operation of a low-solidity highly loaded turbine-blade profile suitable for use in an air-cooled turbine, which has been made in a cascade.

Report presenting an investigation at transonic speeds of the control balancing characteristics of three tabs on a full-span flap on an aspect-ratio-3, 45 degree sweptback wing. The results indicated that all the tabs tested, inset, attached, or detached, would balance the flap hinge moments throughout the speed range.

Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.

Report presenting a study of the storage properties of fuming nitric acids, with and without additives, at 170 degrees F in closed containers of aluminum bodies and steel caps. The effects on the storage properties indicated that the potassium fluoride dihydrate is most effective in reducing the rate of pressure rise and reducing corrosion on aluminum and stainless steel surfaces.

A low-speed wind-tunnel investigation was made to determine the lateral control characteristics of a series of untapered low-aspect-ratio wings. Sealed flap ailerons of various spans and spanwise locations were investigated on unswept wings of aspect ratios 1.13, 1.13, 4.13, and 6.13; and various projections of 0.60-semispan retractable ailerons were investigated on the unsweptback wings of aspect ratios 1.13, 2.13, and 4.13 and on a 45 degree sweptback wing. The retractable ailerons investigated on the unswept wings spanned the outboard stations of each wing; whereas the plain and stepped retractable ailerons investigated on the sweptback wing were located at various spanwise stations. Design charts based on experimental results are presented for estimating the flap aileron effectiveness for low-aspect-ratio, untapered, unswept.

Abstract: An ionization chamber to monitor air for beta activity is described. Operating curves are given, as well as results of shock and vibration tests. Recommendation for improved design are included.

Abstract: "Preliminary data have been taken to evaluate X-ray absorption at the L III edge of uranium as a method of detection of uranium in solution. Uranium concentrations in water from 150 ppm to 30,000 ppm have been investigated. The effect of copper as a typical contaminant in the range of 737 ppm of copper to 36,850 ppm of copper has been investigated for a representative uranium solution. Instrumentation has been constantly improved and suggestions for further improvements in amplifying and counting equipment are included. Comparison of experimental data with theory indicates that the derived equations are adequate."

The following report describes data on the provided phase equilibrium systems that show the general nature of the diagrams and the compounds and solid solutions which occur.

The [beta] spectrum of the 10-year Pu²⁴¹ was run on a sample of radiochemically pure plutonium containing the isotopes Pu²³⁹, Pu²⁴⁰, Pu²⁴¹, isotopically enriched in Pu²⁴¹ by pile neutron irradiation. The isotopic composition was determined mass spectrographically.

Report discussing the progress of various research projects by members of the Mathematics Panel at Oak Ridge National Laboratory for the quarter ending October 31, 1951.

Summary of progress on various research projects conducted during January, 1952.

The question has arisen of how the beam in A-12 as a long resonant cavity might effect the frequency of operation and the field distribution. This study is published to make available the calculation of the direct beam effect as an illustration of general methods of attacking perturbing effects in resonant cavities.

From Summary: "A simple method is presented for estimating lift, pitching-moment, and hinge-moment characteristics of all-movable wings in the presence of a body as well as the characteristics of wing-body combinations employing such wings. In general, good agreement between the method and experiment was obtained for the lift and pitching moment of the entire wing-body combination and for the lift of the wing in the presence of the body. The method is valid for moderate angles of attack, wing deflection angles, and width of gap between wing and body."