Report issued by the Brookhaven National Laboratory discussing progress of waste concentration studies. As stated in the introduction, "the present report covers all experimental hot runs up to the time the still was turned over to the Waste Control Section for intermediate handling of laboratory D waste" (p. 1). This report includes tables, illustrations, and photographs.

From abstract: "This program was a study of the basic variables that affect electrostatic classification of heterogeneous aerosols of submicron size, especially below 0.1 [mu]."

The following quarterly report covers the period from May 16 to August 15, 1962. This report summarizes the progress being made on the study of the saturation and recovery of the hole which can be burned into the magnetic resonance band associated with the F-center in KCl.

From introduction: Silicon carbide is being considered as a basis material for nonmetallic fuel elements because of its high thermal conductivity, low nuclear cross section, high resistance to thermal rupture, and high degree of stability at high temperature in air. A requirement of the fuel elements is that they be thin and have as low porosity as possible. One shape of element under consideration is 0.050 to 0.070 inch thick by a few inches in width and breadth.

This report discusses three experimental methods used to study the kinetics of the reaction between zirconium and UO2.

The following report describes the process to determine the method for determination of americium in the presence of plutonium and uranium.

This report presents data recorded during a program made to improve uranium slug quality in January, 1952, to determine what improvements could be made in the welding process.

Abstract. the electrodeposition of uranium metal, in the form of tree-like deposits, from molten strontium halide baths is described. Under the best conditions studied, approximately 40% recovery is attained. Freedom from side-reactions of the reduced uranium with anode products and/or refractory materials, and high cathode current densities appear to be essential to the success of the process. the refining of uranium under similar conditions appears to occur quite readily, with approximately 50% current efficiency. The preparation of UI3 is also described.

This memorandum constitutes a final report of the study performed at the U. S. Waterways Experiment Station on a model of the outlet works for the Wappapello Dam The model was built undistorted to the linear scale ratio, model-to-prototype, of 1 to 25. The general purpose of the model study was to check the hydraulic characteristics of all elements in the design of the outlet works, and to develop means of correcting any uneconomic, unsafe, or undesirable conditions.

Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.

Memorandum presenting an investigation carried out in the 11-inch hypersonic tunnel to determine the static longitudinal and lateral stability and control characteristics of an airplane configuration with a trapezoidal wing with a modified hexagonal airfoil section and equipped with various tail airfoil sections and tail arrangements. The tests were made at Mach number 6.86 and Reynolds number 343,000 based on the wing mean aerodynamic chord.

Report presenting results from a flight program conducted to obtain information on the airplane response and actual rates and amounts of control motion used by service pilots to perform squadron operational training missions, which are correlated with the airplane handling qualities and calculated maximum dynamic response. Results regarding longitudinal characteristics, rolling characteristics, and sideslip characteristics are provided.

Memorandum presenting a generalized analysis of the effects of turbojet propulsion system development and fuel selection on ability of a strategic bomber to perform desired and minimum missions. The variation of bomber performance using a hydrocarbon, boron, or nuclear fuel is discussed.

Memorandum presenting a computation and comparison of the thrust augmentation and accompanying total fuel flow for four afterburner fuels and a rocket. Four turbojet engines burning JP-4 primary fuel and several operating conditions were selected for the analyses.

Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain operating conditions the flame extended beyond the turbine position.

Report presenting an investigation of the experimental performance of chlorine triflouride and hydrazine measured over a range of propellant mixtures in a 100-pound-thrust rocket engine. Experimental values of specific impulse, volume specific impulse, heat rejection per propellant weight, nozzle thrust coefficient, and characteristic velocity were obtained as functions of percent fuel by weight in the propellant mixture.

Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.

Report presenting the horizontal-tail load measurements obtained during testing of the Bell X-5 airplane at the NACA High-Speed Flight Research Station. Measurements were taken at a range of Mach numbers and from sweep angles of 20 degrees to 59 degrees.

An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.

Report discussing factors influencing flight range and aerodynamic heating for hypersonic boost-glide aircraft. The possibility and advantages of flight at very high altitude to reduce aerodynamic heating and encourage the preservation of laminar flow on the surface of the aircraft is explored.

The methods used to prepare and purify 19 hydrocarbon derivatives of cyclopropane are discussed. Of these hydrocarbons, 13 were synthesized for the first time. In addition to the hydrocarbons, six cyclopropylcarbinols, five alkyl cyclopropyl ketones, three cyclopropyl chlorides, and one cyclopropanedicarboxylate were prepared as synthesis intermediates. The melting points, boiling points, refractive indices, densities, and, in some instances, heats of combustion of both the hydrocarbon and nonhydrocarbon derivatives of cyclopropane were determined. These data and the infrared spectrum of each of the 34 cyclopropane compounds are presented in this report. The infrared absorption bands characteristic of the cyclopropyl ring are discussed, and some observations are made on the contribution of the cyclopropyl ring to the molecular refractions of cyclopropane compounds.

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. Transition was observed by means of a hot-wire anemometer located at various chordwise stations for each position of the roughness. These observations indicated that when the roughness is sufficiently submerged in the boundary layer to provide a substantially linear variation of boundary-layer velocity with distance from the surface up to the top of the roughness, turbulent "spots" begin to appear immediately behind the roughness when the Reynolds number based on the velocity at the top of the roughness height exceeds a value of approximately 600. At Reynolds numbers even slightly below the critical value (value for transition), the sandpaper type of roughness introduced no measurable disturbances into the laminar layer downstream of the roughness. The extent of the roughness area does not appear to have an important effect on the critical value of the roughness Reynolds number."

From Introduction: "This report makes further comparisons of the theoretical computing method with available experimental results, showing effects of wing plan-form changes, and the effect of an airfoil-section change on a wing of given plan form."

Report presenting investigations of a full-scale air-cooled aircraft-engine cylinder of 202-cubic-inch displacement to determine the effects of internal cooling by water induction on the maximum permissible power and output of an internal-combustion engine. Results regarding the maximum permissible engine performance, engine temperatures, and constant inlet-air pressure investigations are provided.