Report issued by the U.S. Bureau of Mines on diesel fuel consumption during the 1950 calendar year. Analysis on 266 samples of diesel fuel and their characteristics are presented. This report includes tables, and a map.

Abstract: "The effects of acidity on extraction of vanadium and molybdenum by diethyl ether are described. Solubility data for several vanadium compounds in nitrate process solutions are presented. Preliminary results on the extraction of uranium from process slurries by tributyl phosphate are reported, including data on the contaminants extracted with the uranium."

From abstract: "Results of tests investigating the effects of feed and scrub acidities on the extraction of uranium and contaminants from process slurries by tributyl phosphate-Gulfspray Naphtha in a Scheibel continuous extractor are described. Studies on the fractional precipitation of MgX from a dilute sulfuric acid system throw considerable light on the probable constitution of MgX. Further data on the effect of acidity on the extraction of molybdenum and vanadium into ethyl ether are presented.

Abstract: Technical report describing an evaluation of solvents for use in the extraction of uranium from Mallinckrodt type ore feeds.

Technical report evaluating solvents for use in the extraction of uranium from Mallinckrodt type ore feeds. Re-evaluates the Mallinckrodt process in the light of the more recent solvent extraction development that has been carried out at various AEC sites.

The coefficients of thermal conductivity of aluminum-bismuth metal-to-metal bonds, and of aluminum and bismuth surfaces in contact under pressure, were measured.

Report documenting the suitability of Nebraska for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest

Introduction: "This paper presents in formula form IBM computational procedure for averaging cross-section data and for calculating reflected spherical reactors by the linear by the linear multigroup numerical method developed by the Physics Section of the ANP Central Design Group. The adjoint reactor numerical procedural is included."

Summary: "The problem of evaporation of secondary radioactive wastes resulting from waste disposal studies at Mound Laboratoy has been studied experimentally to determine the fundamental design characteristics of a plant size unit. Emphasis, of course, was on decontamination, but the factors affecting foaming and scaling also had to be investigated and evaluated. Generally speaking, the final design is a standard type of evaporator, the only unique feature being the relation of the two effects. Where critical, as affecting performance, the particular design features have been specified."

Report presenting a graphical method for obtaining the two-dimensional supersonic flow with moderate heat addition. The basic equations were derived for flows in which the total temperature has a continuous variation with displacement in the direction of the flow.

Note presenting general differentiation formulas for successive derivative of a function, which are obtained in terms of the values of the function at unequally spaced arguments and the corresponding distances between the successive arguments using Lagrangian polynominals of various degrees. A general discussion of applying the formulas to the numerical solution of partial differential equations is made.

Report presenting an experimental investigation of the effect of several oil introduction parameters on the temperature of 75-millimeter-bore cylindrical-roller, inner-race-riding cage-type bearings over a range of DN values and static radial loads with single-jet circulating oil feed. Results regarding effect of radial location of oil jet, angle of impingement, effect of jet diameter, power required for oil delivery, and velocity effect are provided.

Report presenting an investigation in the free-flight tunnel for the purpose of comparing the dynamic lateral control characteristics of airplane models with round- and sharp-leading-edge wing sections. The two dynamic models used in the investigation had different mass characteristics and had different types of inertia. Results regarding the interpretation of flight-test results, high-inertia model, and normal-inertia model are provided.

Note presenting a theoretical investigation made to determine the effect of nonlinear stability derivatives on the lateral stability of the airplane. The results indicated that under certain conditions, a motion is obtained which has different rates of damping for the large and small amplitudes of motion, with very little damping at the small amplitudes.

Note presenting an analysis of the flow around cones without axial symmetry and moving at supersonic velocity. The results of the analysis are applied to the determination of flow around circular cones at small angles of attack. It is shown that good agreement with experimental results can be obtained from the first-order theory if the complete equation for the pressure distribution is used.

Note presenting a method of visualizing air-flow patterns by observing the motion of finely divided particles of balsa wood introduced into the air. Photographic results obtained by this method for small-scale models of several helicopter rotor configurations in the static-thrust condition are presented. The results indicate the feasibility of using the balsa-dust technique for obtaining useful qualitative information on the air-flow patterns for transient conditions as well as for steady-state conditions.

Report presenting a wind-tunnel investigation of a series of modifications to the leading-edge region of the NACA 63(sub 1)-012 airfoil section to determine the possibilities of delaying the flow separation that occurs near the leading edge of the basic section and improving the stalling characteristics. Results regarding the effect of the leading-edge modifications and effect of leading-edge flap are provided.

Note presenting an investigation made in the 300 mph 7 - by 10-foot tunnel to determine the effects of various sizes and shapes of end plates on the aileron characteristics and on the aerodynamic characteristics in pitch and yaw of a wing of aspect ratio 2 with no taper and a sweepback of 45 degrees and of a wing of aspect ratio 4, taper ratio 0.6, and sweepback of 46.7 degrees. The addition of end plates to the swept wings increased the lift-curve slope, reduced the maximum lift-drag ratio, generally decreased the maximum lift coefficient, and increased the longitudinal stability slightly in the low lift coefficient range.

Note presenting the application of a new back-reflection X-ray diffraction technique, which was developed through use of a multiple-film camera containing four parallel films separated by known distances. Diffraction angles were calculated by determining the change in radius of the diffraction ring from film to film. A multiple-film-technique analysis and a conventional-method analysis of the same X-ray strain data indicated that a more detailed analysis of atomic strain could be obtained from the multiple-film technique.

"Differential equations and boundary conditions are derived for the bending and buckling of sandwich plates. The buckling load is calculated for a simply supported plate subjected to edgewise compression. The formulas are evaluated numerically and the results are plotted in a diagram" (p. 1).

Report presenting a method for the approximate calculation of the stresses and distortions in a box beam representing the main structural component of a swept wing with a carry-through section and with bulkheads perpendicular to the spars. Results regarding determination of shear-leg effects, effect of bulkhead flexibility, and extension of the method are provided.

Note presenting a wind-tunnel investigation of the NACA 64A010 airfoil section to determine the boundary-layer and stalling characteristics at low speed. The tests were made at a Reynolds number of 4.1 million and included force measurements, pressure-distribution measurements, flow studies by the liquid-film technique, and boundary-layer measurements.

"A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number of 1.62" (p. 1).

Report presenting measurements of elevator-stabilizer effectiveness and trim of the X-1 airplane at 40,000 feet altitude at a range of Mach numbers and normal-force coefficients.