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1. Summary of Runs, s56, 57, 73, 74, 78, 79, 80, 87, 88, 89 in Which Slurries Circulated at 300 C in 100-a Loops Caked or Accumulated on Pipe Walls. 2. Summary of Runs T-52 Through T-75 in Which a Bypass Line Was Used in Parallel With Main Circulating Loop
No Description Available.
200 Area waste storage study
As a part of the five year budget study requested by HOO-AEC, a study of separations waste storage requirements for this period was made. This study took into consideration the variant estimates of amount of irradiated uranium to be processed, and the goals in the waste reduction research and development program. The conclusions of this study were at variance, to some extent, with prior studies. Interest has been expressed in publication of this study to permit independent assessment of its bases and assumptions.
327 Basin Aluminum Corrosion Test
An investigation of corrosion in the 327 Building's water storage basin was made to determine whether the static storage of aluminum jacketed fuel elements could cause corrosion effects that would interfere with studies of in-pile corrosion.
600 MW Fused Salt Homogeneous Reactor Power Plant
This report is a study of the feasibility of using a fused salt fuel reactor in a central station electric generating plant.
1955 at Hanford
This document summarizes activities of the Hanford Atomic Products Operation during 1955.
ABSOLUTE BETA ASSAY WITH END-WINDOW GEIGER-MUELLER COUNTERS
No Description Available.
Absolute Cross Sections for Secondary Particles Produced in High-Energy Nuclear Bombardments
From abstract: Absolute cross sections for the production of charged secondary particles is the bombardments of aluminum, nickel, silver, and gold by 332-Mev protons, 187-deuterons, and 380-Mev alpha particles have been determined.
Absorption by Soil of Strontium From 216-S Crib Waste
A preliminary soil column experiment with a waste sample from the 207-S-11 well, which monitors the 216-S cribs, indicated that cesium was absorbed almost completely by the soil but that strontium breakthrough to ground water in the near future seemed likely. Accordingly, it was suggested that the 216-S wastes be discharged to a new disposal site, and that samples of the wastes which are currently being discharged to the 216-S cribs be obtained for soil absorption tests. The primary purpose of these tests was to obtain data which could be used to suggest ways and means of improving the absorption of strontium by soil from the process condensate stream (D-2_ and the cell drainage stream (D-1), both of which have been discharged to the 216-S cribs for the past several months.
Absorption Spectra of Aromatic Disulfides
The effect of solvents and temperature on the optical absorption spectrum of a number of substituted aromatic disulfides is reported. The problems offered by the disulfide link and the exchange reactions between disulfides, and between disulfides and thiols, are receiving increasing attention. Recently the base-catalyzed exchange between various alkyl disulfides and the corresponding thiols was studied by means of a radioactive-tracer technique. Our initial purpose was to extend these investigations to a large number of compounds in a variety of experimental conditions using a spectrophotometric technique that, if applicable, would have been incomparably faster.
The Absorption Spectra of Complexes of Uranium (VI) with Some [beta]-Diketones
Abstract: "The absorption spectra of the complexes of uranium (VI) with four [beta]-diketones were determined under various conditions of pH, concentration of uranium, and alcohol concentration. Under optimum conditions, the maximum molar absorptivity (31,200) is obtained using 2-furoyltri-fluoroacetone. This compares with about 4,000 and 19,000 for the thiocyanate and dibenzoylmethane complexes, respectively."
Absorption Spectra of Lanthanide and Actinide Rare Earths. [Part] 3. The Heavier Lanthanide Elements in Aqueous Perchloric Acid Solution
No Description Available.
Absorption Spectra of Plutonium and Impurity Ions in Nitric Acid Solution
The absorption spectra for Pu(III), (IV), (VI), and the red Pu(IV)- peroxy complex were determined in HNO/sub 3/ solution. Extinction coefficients for the above species of Pu were measured. Temperature has little effect on the spectra, but variation of acidity causes shifting of absorption peaks and some changes in the extinction coefficients. The absorption spectra and extinction coefficients in the region 390 to 1200 m mu were measured for chromic, nickelous, manganous, calcium, lanthanum, aluminum, ferrous. ferric, and permanganate ions in HNO/sub 3/ solutions. In addition, the effects of nitrite, oxalic acid, sulfamic acid, hydrogen peroxide, and various HNO/sub 3/ concentrations on the extinction coefficients of some of these ions were determined. The chromic, nickelous, ferrous, and permanganate ions, and ferric ion with oxalic acid, have sufficiently high extinction coefficients to cause inaccuracies in valence determinations of Pu in solutions containing high concentrations of these ions, unless corrections are made. (auth)
Abstract Summary and Subject Index of Preliminary Reports, Analytical Chemistry Division, X-10 Site, January - June, 1956
This report is a compilation of brief abstracts of the Preliminary Reports n work done in the laboratories of the Ananlytical Chemistry Division at the X-10 Site during the months of January through June, 1956.
Abundance and Distribution of Uranium and Thorium in Zircon, Sphene, Apatite, Epidote, and Monazite in Granitic Rocks
The following report covers investigations of uranium and thorium discovered within host minerals in the earth's crust, zircon, sphene, apatite, epidote, and monazite. The object of this investigation has been to obtain an approximate measure of the abundance and distribution of uranium and thorium among these five mineral phases.
The Accuracy of the Substitute-Stringer Approach for Determining the Bending Frequencies of Multistringer Box Beams
"The accuracy of the substitute-stringer approach for including the effects of shear lag in the calculation of the transverse modes and frequencies of multistringer box beams is investigated. Box beams, the covers of which consist of normal-stress-carrying stringers on sheets which carry not only shear but also normal stress, are analyzed exactly. Frequencies of beams with various numbers of stringers, obtained by means of this exact analysis, serve to determine the possible accuracy of the frequencies obtained by the substitute-stringer approach" (p. 1).
Acoustics of a Nonhomogeneous Moving Medium
Report discussing theoretical basis of the acoustics of a moving nonhomogeneous medium. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included.
ACTIVE CATION TRANSPORT IN SUBMERGED AQUATIC PLANTS. I. EFFECT OF LIGHT UPON THE ABSORPTION AND EXCRETION OF CALCIUM BY POTAMOGETON CRISPUS (L) LEAVES
No Description Available.
Active Process Development Activities for Processing of Feed Materials
The carbonate and organic leaching processes for the recovery of U from its ores are outlined. The Excer prccess (ion-exchange conversion and electrolytic reduction) and the Fluorox process (starch-- HF reaction) for the production of UF/sub 4/ from ore concentrate and depleted reactor fuels are described. The fluidized-bed process for UF/sub 4/ production from UO/sub 2/(NO/ sub 3/)/sub 2/ is also described. Methods for improving the reactivity of UO/sub 3/ and mechanical and thermal processes for increasing the density of UF/sub 4/ were investigated. Applications of fluoride volatility prccesses to feed materials are discussed. (C.W.H.)
ACTIVITIES IN LIQUID AND SOLID BINARY METAL SYSTEMS. Progress Report on Research Program for February 1, 1956 to January 31, 1957
No Description Available.
Acute Lethality of Partial Body in Relation to Whole Body Irradiation
No Description Available.
Adaptation of Combustion Principles to Aircraft Propulsion Volume 2: Combustion in Air-Breathing Jet Engines
This volume continues the NACA study of combustion principles for aircraft propulsion. The various aspects of combustion pertinent to jet engines are organized and interpreted with quite extensive information, particularly for basic or fundamental. subject matter. The report concerns only air-breathing engines and hydrocarbon fuels, and not rocket engines and high-energy fuels.
Addendum to DC 56-8-167
This document is an addendum to DC 56-8-167 and gives a description of the proposed Navy nuclear seaplane program and the objectives of the X211 engine study program.
Additional Analysis of SRE Safety
AI-MEMOS are working papers and may be expanded, modified, or withdrawn at any time, and are intended for internal use only. Further dissemination is not permitted and distribution to abstracting agencies is not authorized.
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
The Adsorption of He3 and He4 on Activated Charcoal
The adsorption on activated charcoal of pure He3 at 2.5 and 3°K, and of pure He4 at 4°K has been measured. The volume of gas necessary to form a monolayer is approximately the same for the two isotopes. It is shown that capillary condensation does not occur in this adsorbent at low saturations. The data have been analyzed by a number of methods with consistent results.
Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight
From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds
Report discussing a flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 of Various Tip Controls on the Wing Panel of a 0.05-Scale Model of a Martin XASM-N-7 (Bullpup) Missile: TED No. NACA AD 3106
"An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the control effectiveness and hinge-moment characteristics of the Martin XASM-N-7 (Bullpup) missile. A half-scale wing panel was tested with a tip control having three different hinge-line locations. The tests were made over an angle-of-attack range from -10 to 10 degrees and a control-deflection range of -15 to 3 degrees" (p. 1).
The Aerodynamic Characteristics in Pitch of a 1/15-Scale Model of the Grumman F11F-1 Airplane at Mach Numbers of 1.41, 1.61, and 2.01, TED No. NACA DE 390
"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231
Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9
Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Aerodynamic control of supersonic inlets for optimum performance
From Introduction: "The purpose of this paper is to discuss and evaluate some of the input signals or control parameters which have been experimentally employed to operate turbojet inlet-control systems. These include the normal-shock position, the oblique-shock position, and the diffuser-exit Mach number. The discussion is based on results obtained at the NACA Lewis laboratory during control investigations of ram-jet engines (ref. 1 to 5) and during a study on the control of a supersonic inlet for the J34 turbojet engine (refs 6 and 7)."
Aerodynamic Damping at Mach Numbers of 1.3 and 1.6 of a Control Surface on a Two-Dimensional Wing by a Free-Oscillation Method
Memorandum presenting tests at two supersonic speeds to obtain experimentally the aerodynamic damping characteristics of a control surface on a two-dimensional wing. The control surface had a chord of 1.67 inches and a span of 7.25 inches and was supplied in three materials with different mass, inertia, and stiffness properties. Results regarding the presentation of data and comparison with theory and comparison with control-surface data for a triangular wing are provided.
Aerodynamic Design of Axial-Flow Compressors: Volume 1
Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.
Aerodynamic Design of Axial-Flow Compressors, Volume 2
"Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).
Aerodynamic design of axial-flow compressors: Volume 3
Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.
Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0
Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64
From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Aerodynamic heating of aircraft components
From Introduction: "The purpose of this paper is to review new and significant data which will be of interest to designers in determining the heating of these components. A comparison with existing theory to indicate its adequacy in each case is also presented."
Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base
Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01
Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.
Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96
Report presenting an investigation to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of an unswept semispan cantilevered wing of aspect ratio 4.0. Results regarding wing loads and store loads are provided.
Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96
Memorandum presenting an investigation in the blowdown tunnel of the pressure tunnel to determine the aerodynamic characteristics of a sting-mounted Douglas Aircraft Company store in the presence of, but not attached to, an unswept semispan cantilevered wing of aspect ratio 4.0. The influence of the store on the aerodynamic characteristics of the wing was also obtained.
Aerodynamic mixing downstream from line source of heat in high-intensity sound field
From Summary: "This report describes a theoretical and experimental investigation of the aerodynamic mixing by a standing sound wave downstream from a continuous line source of heat."
Aerodynamic principles for the design of jet-engine induction systems
From Introduction: "It is the purpose of this report to assemble principles of induction-system design for flight to a Mach number of 2 and to use existing data to show the consequences of compromising them."
Aerodynamic Principles for the Design of Jet-Engine Induction Systems
Jet engine induction systems investigations and relationship of air inlets, drag, airframe, pressure recovery, flow and interferences.
Aerodynamics of bodies, wings, and wing-body combinations at high angles of attack and supersonic speeds
From Introduction: "The primary purpose of this paper is to describe progress in the aerodynamics of wings, bodies, and wing-body combinations at high angles of attack."
Aerodynamics of Missiles Employing Wings of Very Low Aspect Ratio
Memorandum presenting wind tunnel tests performed on a family of missiles. This paper summarizes some of the performance and stability and control characteristics of the missiles.
Aeroelastic Problems of Airplane Design
The technical memorandum briefly summarizes the growth of interest in aeroelastic phenomena as aircraft speed increased and wing designs changed for faster aircraft. Different types of aircraft vibrations are then introduced, and the mathematical basis for the theory behind them is described. Special attention is given to static oscillations, wing flutter, and the flutter of skin panels. The last section of the memorandum deals with the prevention of flutter by design specifications.
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