This report explores the production of beta silicon carbide, a low-temperature, cubic modification of cubic silicon carbide. The temperature, heating time, type of starting material, and proportion of starting materials were all varied in order to test yields of beta silicon carbide.

Summary: A study has been made of possible processes for the production of hafnium-free zirconium of a grade suitable to meet AEC specifications.

From operational program: This final report includes a general geologic description of the area, including descriptions of the various geologic units and correlates the airborne data to the geologic units as provided by the geologic maps. Also included is a frequency distribution study of the data as a function of the geologic units encountered over the NTMS area including the tie line data. This report also consists of a discussion of the area surveyed and includes all single record reduced data and averaged record data listings on microfiche.

"This report describes the results of a comprehensive study of plastic deformation of aluminum single crystals over a wide range of temperatures. The results of constant-stress creep tests have been reported for the temperature range from 400 degrees to 900 degrees F. For these tests, a new capacitance-type extensometer was designed. This unit has a range of 0.30 inch over which the sensitivity is very nearly linear and can be varied from as low a sensitivity as is desired to a maximum of 20 microinches per millivolt with good stability" (p. 353).

An investigation is being conducted to determine the feasibility of studying aileron buzz by means of the wing-flow method. Two semispan models which had an aspect ratio of 6 and a taper ratio of 2 with quarter-chord half-span mass-balanced ailerons have been used. One had an NACA 23012 airfoil section and the second, an NACA 65-212 airfoil section. The ailerons on both models were subject to buzz over a small range of Mach number near 0.9. Data obtained by wing-flow testing agreed reasonably well with full-scale flight results.

From Introduction: "An analytical method for estimating turbine performance from the blade angle8 and flow areas was therefore developed at the NACA Lewis laboratory and is described herein."

From Introduction: "The performance of several tail-pipe burners with fixed area exhaust nozzles is reported in references 1 to 4, and the performance of an NACA-designed tail-pipe burner with a variable-area exhaust nozzle is reported in reference 5. Operational characteristics of the tail-pipe burner are also discussed."

An approximate method is presented for the calculation of the external lift, moment, and pressure drag of slender open-nose bodies of revolution of supersonic speeds. The lift, moment, and pressure drag of a typical ram-jet body shape are calculated at Mach numbers 1.45, 1.60, 1.75, and 3.00; and the lift and moment results are compared with available experimental data. The agreement of the calculated lift and moment data with the experimental data is excellent. The pressure-drag comparison was not presented because of the uncertainty of the amount of skin-friction drag present in the experimental results.

From Introduction: "An analytical method for estimating turbine performance from angles and flow areas was therefore developed at the NACA Lewis laboratory in 1947 and is described herein."

"A theory has been developed for resetting the blade angles of an axial-flow compressor in order to improve the performance at speeds and flows other than the design and thus extend the useful operating range of the compressor. The theory is readily applicable to the resetting of both rotor and stator blades or to the resetting of only the stator blades and is based on adjustment of the blade angles to obtain lift coefficients at which the blades will operate efficiently. Calculations were made for resetting the stator blades of the NACA eight-stage axial-flow compressor for 75 percent of design speed and a series of load coefficients ranging from 0.28 to 0.70 with rotor blades left at the design setting" (p. 425).

This report follows ciritical-assembly studies on: the effect on reactivity caused by changes in axial reflector materials; the effect on reactivity and the power perturbation caused by fast safety control-blade guides; the effect of changes in fuel-element material composition; the effect of changes in fuel-elements spacing designed to produce uniform radial power-generation rates.

Report discussing "the reduction of uranium(VI) with a slight excess of chromous sulfate followed by a potentiometric titration of the uranium(IV) with standard ceric sulfate in an atmosphere of carbon dioxide." This method cannot be used at room temperature.

From introduction: The present report is a summary of the experimental work on a laboratory scale to date involving the ammonia reduction and the one step TF4 processes.

Abstract: "These data are presented by element in part I, and all 39,000 observed lines are given in order of wavelength in Part II." From Introduction: "In the beginning, most intensity data were reported on an arbitrary scale of 10 steps, weak lines being assigned an intensity of 1, and the strongest line intensity 10."

From introduction: "This report covers work performed in the Solid State Division for the quarter ending May 10, 1952." Topics covered include radiation metallurgy, engineering properties, solid state reactions, crystal physics, and special projects.

"The flight investigation of the C-54D airplane was initiated to determine the necessity of changes or additions to existing handling-qualities requirements to cove the case of instrument approaches with large airplanes. This paper gives a brief synopsis of the results and presents the measured data of tests to determine the stability and control characteristics. It was found that no new requirements were necessary to cover the problems of instrument approaches" (p. 1).

Calibrations of the Friez Aerovane, Wind Measuring Set AN/GMQ-11, manufactured by the Friez Instrument Division of the Bendix Aviation Corporation, were made in the Langley 300 MPH 7- by 10-foot tunnel at the request of the Signal Corps, U, S. Army. Two propellers snd two generators were tested through a speed range of 15 to 190 knots, The results indicated that at airspeeds greater than 80 knots the instrument indicated airspeeds higher than the tunnel airspeed..

Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude stabilization system with proportional control for certain nonlinear pitching-moment variations and autopilot adjustments.

"An investigation of the suitability of the N.A.C.A. Roots type aircraft engine supercharger to flight-operating conditions, as determined the effects of the use of the supercharger upon engine operation and airplane performance, is described in this report. Attention was concentrated on the operation of the engine-supercharger unit and on the improvement of climbing ability; some information concerning high speeds at altitude was obtained. The supercharger was found to be satisfactory under flight-operating conditions. Although two failures occurred during the tests, the causes of both were minor and have been eliminated" (p. 207).

This bibliography contains 37 references on self-shielding cross sections. The bibliography is limited to the period from 1951 through November 1959 with the references arranged alphabetically by title. The sources used in compiling this bibliography were: Abstracts of Classified Reports Nuclear Science Abstracts

A chemical flowsheet is proposed for recovery of strontium and rare earths from Purex wastes. The iron in the waste is first complexed with tartrate and the pH is adjusted with caustic. Strontium and rare earths are extracted by a solvent comprised of di(2-ethylhexyl)phosphoric--sodium di (2-ethylhexyl) phosphate--tributyl phosphate -- Amsco 125-82. and are stripped with nitric acid. Processing the strip product through additional solvent extraction cycles yields isolated, concentrated strontium and rare earth fractions.

After shutdown heating rates have been calculated for the target, control plates, and the beryllium reflector of the HFIR. Hilvety previously calculated the after shutdown heating rates in the element and his results are reported in ORNL CP-60-4-110. Decay times of 1.0 10, 10^2, 10^3, 10^4, and 10^5 seconds have been considered, and heat fluxes have been computed for all of the mentioned components. The greatest heat fluxes were found to be at the surfaces of the control plates and the permanent beryllium reflector.