Abstract: "The sensitivity to fast neutrons of a CP Meter ionization chamber of the type used for health physics beta and gamma survey measurements has been investigated."

Abstract: "The solubility of oxygen in uranyl sulphate solutions and in water at 212, 275, and 325 F, and at oxygen partial pressures up to 1500 psia was investigated. The results are presented in tabular and graphic form. The solubility is proportional to the partial pressure of oxygen. The ratio of solubility in the uranyl sulphate solution to solubility in water at the same temperature and pressure is a function of the concentration of the salt in solution."

This document is the third in a series of progress report that records investigations of graphite bodies. Along with the report, two appendices are given to describe the different graphite bodies: "Synthetic Binders for Carbon and Graphite" and "High Temperature Physical Properties of Molded Graphites".

Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep. Application of the method is demonstrated for 58 cases covering various types of flaps on wings with a wide range of sweep, aspect ratio, and taper ratio.

Memorandum presenting the results of some investigations of separation on heat transfer and a method of reducing separation and shows the heat transfer in regions of separation and reattachment for a few specific shapes. The results show that heat transfer in a separated region is strongly affected by the extent of separation, the location of the reattachment point, and the location of transition along the separated boundary.

Free oscillation test to determine hinge moment of trailing-edge, flap control surface with various hinge-line positions at transonic speed. Results show that oscillating amplitude has a large effect on the control aerodynamic damping derivative and that the damping is unstable in the test Mach number range above about 0.90 for the hinge positions tested.

"An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and split-flap-type ailerons deflected plus or minus 15 degrees" (p. 1).

Report presenting an investigation of the distribution of pressure at zero lift over the surface of a swept airfoil of biconvex section. The measured pressures are compare with theoretical values calculated from thin-airfoil theory. Results regarding pressure distributions, drag, and boundary-layer studies are provided.

Report presenting an investigation of a family of turbine-rotor-blade designs based on one-dimensional-flow theory and incorporating systematic changes in design variables. They were designed for 40-percent reaction and a total-to-static pressure ratio of 4.00 based on the assumption of constant static pressure along the radius and one-dimensional-flow theory for the design of the rotor-blade passages.

From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."

Report presenting an investigation of systematic series of sharp- and blunt-trailing-edge wings to determine the effects of thickening the trailing edges on the lift, drag, and pitching moment characteristics at several Mach numbers. Results indicate that no appreciable zero-lift drag reduction can be obtained by thickening the trailing edges from 1.41 to 1.96, but trailing edges can be thickened appreciably with no increases in zero-lift drag.

Report presenting a wing-flow investigation to determine the lift, pitching-moment, and hinge-moment characteristics of an unswept and untapered NACA 65-009 airfoil model with an aspect ratio of 3.01 and a 1/4-chord full-span plain flap. Effects of sealing a portion of the length of the flap gap were investigated as well as adding roughness to a portion of the airfoil chord. Information about the maximum unstalled lift coefficient, compressibility phenomenon, and hinge-moment coefficient is also provided.

"Preliminary measurements have been made of velocity and temperature fluctuations in the flow behind a heated grid in a uniform airstream. Temperature correlation shows a reasonable degree of isotropy, and the temperature fluctuations die out at large distances more slowly than the turbulence, as has been predicted theoretically under some strongly simplifying postulates" (p. 1).

Report presenting an experimental investigation in the 7- by 10-foot tunnel in a range of Mach numbers to determine the drag and opening characteristics of a model of a Kaman Aircraft Corporation Rotochute. The Rotochute is a two-bladed flapping rotor with governor-controlled blades designed for lowering cargo containers from high-speed aircraft tested at various Mach numbers simulating constant rates of descent.

Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the effects of a cold exhaust jet on the pressure loadings of an all-movable, 45 degree sweptback horizontal stabilizer located in a region influenced by the jet. Results indicated that at jet pressure ratios of 1 to 9, the exhaust jet did not appreciably affect the pressure loadings of the stabilizer.

Report presenting the performance of slurries of 50 percent boron in MIL-F-5624A grade JP-4 fuel evaluated in a 5-inch ramjet burner. Boron slurries were found to give higher heat outputs than JP-4 fuel only at fuel-air ratios above stoichiometric for JP-4 fuel. Testing found that it was also possible to determine the flow properties of particular batches of slurry before burning by flowing them through a bench system which would simulate the actual fuel system that would use the slurry.

Report discussing tests of the fissionability and capture cross-section of produced U²³².

The following report examines a set of beryllium metal rods through pile radiation, taking measurements, and analyzing differences between irradiated and radiated rod samples.

Abstract: "A model is presented for radiation damage to ductile metals that accounts qualitatively for the effects of radiation on the electrical and mechanical properties. The model consists of an agglomeration of interstitially displaced atoms into stacking faults in the lattice."

Discussing a reconnaissance of uranium-bearing deposits in the Yampa River Region, in Colorado

The purpose of this study was to develop equations for calculating fision product heating in the HRT-CP underflow pot from measured temperatures and to attempt to correlate the rat of solids accumulation in the underflow pot with fission heating and reactor power. Using fission heating data calculated from relating solids accumulation and heating have been tested. In one case an error of no greater than 26% was incurred in the calculation of the total weight of solids collected during chemical plant runs 17-4, 17-5, and 17-6. Further development work will be done on this correlation.

The general program established at Argonne National Laboratory in connection with the Fast Power Breeder Reactor (PBR) includes performance of exponential experiments on assemblies having compositions which may exist in the reactor core. This report deals with that phase of the program known as the Fast Exponential Experiment which may be described very briefly as follows. An assembly of fissile (U-235) and fertile material (too small to be self-critical) intermixed with poisons (such as are encountered in the mechanical structure and coolant system of a self-sustaining reactor) is fed with neutrons from an auxiliary source. By measurements of the neutron flux within the assembly, important parameters can be calculated which are necessary to the proport design of an actual critical reactor of the same composition.

This summary of the research progress meeting on June 10, 1948 discusses the following topics: (1) 184-inch cyclotron (J. Vale); (2) Slow neutrons in the shielding of the 184-inch cyclotron (W. Benson); and (3) Fission of thorium with alpha particles (A. Newton).

Abstract. By means of the pulse radiolysis technique a short-lived transient species has been observed in irradiated de-aerated ethanol and methanol, exhibiting an optical absorption throughout the visible and near infra-red. This transient is suggested to be the solvated electron on the basis of the nature of the spectrum, the reactivity with hydrogen ion and with various organic electron acceptors, and the formation of mononegative ions of some of these acceptors. The absolute rate constants have been determined for the reactions of the solvated electron with hydrogen ion, oxygen and benzyl chloride in ethanol and methanol. The diphenylide ion was found to be short-lived in ethanol. The absolute rate constant for the first-order decay of the diphenylide ion has been determined.