This technical report provides a general description of the Brookhaven National Laboratory, describing the nuclear characteristics of the Brookhaven reactor and more detailed descriptions of the features and instrumentation of the reactor.

Abstract. Spectrographic procedures for determining small amounts of the common contaminants in beryllium and its compounds are described. Suggestions relative to the preparation of synthetic standards are also given.

A report regarding the irradiation behavior of Unalloyed hypostoichiometric uranium carbide experiment AI 3-11 and review

"An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions" (p. 339).

"Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice" (p. 1).

Report presenting an investigation of some effects of aileron spanwise location and wing structural rigidity on the rolling power of 0.3-chord plain, flap-type ailerons on a wing with a taper ratio of 0.25, an aspect ratio of 3.5, and swept back 63 degrees at the leading edge. Results regarding the aeroelastic effects and aileron span and spanwise location are provided.

Report presenting measurements of wing and fuselage pressure distributions made at low and high subsonic Mach numbers on a scale model of the projected X-3 research airplane. Tests were conducted in pitch and yaw and included measurements of the total pressure in the fuselage boundary layer at the location of the left boundary-layer bleed scoop.

Report presenting propeller-blade torsional-deflection data obtained during an investigation of the pressure distribution on constant-chord solid aluminum-alloy blades differing only in camber and thickness. Testing indicated that thinner blades were able to produce greater amounts of deflection. Results regarding torsional deflections are also provided.

Report presenting results from a limited flight program to obtain information on airplane response and actual rates and amounts of control motion used by service pilot in performance of squadron operational training. Results regarding control deflection, control rates, airplane angular velocities, airplane angular accelerations, angle of attack and angle of sideslip, airplane load factors, and airspeed and altitude are provided.

"During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).

Investigation of the effect on zero-lift drag of varying the size and number of symmetrically mounted nacelles on a 45 degree sweptback wing and body combination as determined by free-flight tests of rocket-propelled models over a range of Mach and Reynolds numbers. The nacelle configuration consisted of a twin-engine nacelle near the fuselage, a combination of single-engine nacelles at the wing tip and fuselage, a large nacelle at the wing tip, and a large nacelle near the fuselage.

Report presenting pressure-drag coefficients and the changes in these coefficients with mass-flow ratio, which have been measured in tests of six open-nose conical cowls at an angle of attack of 0 degrees. Testing occurred in the Ames 8 by 8-inch supersonic wind tunnel at a range of Mach numbers. Results regarding pressure distributions, change in cowl pressure drag with mass-flow ratio, cowl pressure drag at a given mass-flow ratio, and changes in cowl pressure drag with mass-flow ratio as a function of Mach number are provided.

Report presenting the zero-lift drag of several wings obtained at supersonic Mach numbers in free flight with rocket-propelled models. The wings tested all had the same exposed area, mounted on the same basic body configuration, and had one of four different types of wings.

The following report examines a rapid method used to eliminate the possibility of explosive perchlorate-organic mixtures in a control laboratory in order to determine radiocesium. These methods include the usage of chloroplatinic acid as a precipitate of radocesium.

Samples containing 5 to 10 mg of uranium were extracted with hexone (methyl isobutyl ketone) and titrated coulometrically in sulphate media. Relative standard deviations of 0.45% for samples containing 5 mg and 0.56% for 10 mg were determined by precision studies.

The initial and long-term nuclear characteristics of two internally cooled heterogeneous, graphite-moderated, two-region, molten-salt reactors have been studied. These reactors have doubling times of 22.5 years and 27.5 years. Methods of decreasing the doubling times by removing the Pa233 from the core and be increasing the specific power of the reactor are described.

From abstract: Results of a reconnaissance geochemical survey of the Rice Lake Quadrangle, Wisconsin are reported. Field and laboratory data are presented for 518 groundwater samples, 540 stream sediment samples, and 533 stream water samples.

From abstract: Results of a reconnaissance geochemical survey of the Iron Mountain Quadrangle, Michigan; Wisconsin are reported. Field and laboratory data are presented for 479 groundwater samples, 369 stream sediment samples, and 389 stream water samples. Statistical and areal distributions of uranium and other possible uranium-related variables are displayed. A generalized geologic map of the survey area is provided, and pertinent geologic factors which may be of significance in evaluating the potential for uranium mineralization are briefly discussed.

From introduction: This is the first in a series of reports describing an investigation of the chemistry of uranium(VI) orthophosphate solutions which is at present underway in this laboratory. Spectrophotometric, potentiometric and solubility studies have been carried out, and it is the first of these which is reported here.

The following report covers the results of a general program that was conducted at the Oak Ridge National Laboratory to investigate the effects on plastic materials of exposure to radiation in the pile. In the investigation, several plastics were irradiated, and on removal from the pile, their rates of decay were determined by measurement of gamma activity in an ionization chamber.

Graphical presentation of he three-phase region at and near the triple point of parahydrogen.

Memorandum presenting an investigation to devise an air-cooled turbine blade which eliminated the difficulties encountered with brazing in air-cooled-blade fabrication. Techniques were developed for casting air-cooled blades with a large number of relatively small cooling passages near the airfoil surface; two such blades of HS-21 material were operated in a turbojet engine modified for air cooling. Results regarding the heat-transfer characteristics, stress and durability results, and evaluation of cast-cored-blade potential are provided.

From Introduction: "This report investigates some of the problems involved in scheduling the tailpipe temperature to avoid stall during acceleration. The object of this report is to investigate the dynamics of a closed-loop acceleration control that follows a schedule of tailpipe temperature with rotor speed."

Report discusses the results of an investigation of a model of a wing of 45 degree sweepback and aspect ratio 6 to determine the aerodynamic characteristics and suction requirements for boundary-layer control by means of area suction applied to trailing-edge flaps. Various flap spans and flap deflections were tested. The measured values of the coefficients were compared to the calculated values.