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Advanced Fuel Cycle Initiative AFC-1D, AFC-1G and AFC-1H End of FY-06 Irradiation Report

Description: The U. S. Advanced Fuel Cycle Initiative (AFCI) seeks to develop and demonstrate the technologies needed to transmute the long-lived transuranic actinide isotopes contained in spent nuclear fuel into shorter-lived fission products, thereby dramatically decreasing the volume of material requiring disposition and the long-term radiotoxity and heat load of high-level waste sent to a geologic repository. The AFC-1 irradiation experiments on transmutation fuels are expected to provide irradiation performance data on non-fertile and low-fertile fuel forms specifically, irradiation growth and swelling, helium production, fission gas release, fission product and fuel constituent migration, fuel phase equilibria, and fuel-cladding chemical interaction. Contained in this report are the to-date physics evaluations performed on three of the AFC-1 experiments; AFC-1D, AFC-1G and AFC-1H. The AFC-1D irradiation experiment consists of metallic non-fertile fuel compositions with minor actinides for potential use in accelerator driven systems and AFC-1G and AFC-1H irradiation experiments are part of the fast neutron reactor fuel development effort. The metallic fuel experiments and nitride experiment are high burnup analogs to previously irradiated experiments and are to be irradiated to = 40 at.% burnup and = 25 at.% burnup, respectively. Based on the results of the physics evaluations it has been determined that the AFC-1D experiment will remain in the ATR for approximately 4 additional cycles, the AFC-1G experiment for an additional 4-5 cycles, and the AFC-1H experiment for approximately 8 additional cycles, in order to reach the desired programmatic burnup. The specific irradiation schedule for these tests will be determined based on future physics evaluations and all results will be documented in subsequent reports.
Date: September 1, 2006
Creator: Advanced Fuel Cycle Initiative AFC-1D, AFC-1G and
Partner: UNT Libraries Government Documents Department

Synthesis and Characterization of Templated Ion Exchange Resins for the Selective Complexation of Actinide Ions

Description: The purpose of this research is to develop a polymeric extractant for the selective complexation of uranyl ions (and subsequently other actinyl and actinide ions) from aqueous solutions (lakes, streams, waste tanks and even body fluids). Chemical insights into what makes a good complexation site will be used to synthesize reagents tailor-made for the complexation of uranyl and other actinide ions. These insights, derived from studies of molecular recognition include ion coordination number and geometry, ionic size and ionic shape, as well as ion to ligand thermodynamic affinity. Selectivity for a specific actinide ion will be obtained by providing the polymers with cavities lined with complexing ligands so arranged as to match the charge, coordination number, coordination geometry, and size of the actinide metal ion. These cavity-containing polymers will be produced by using a specific ion (or surrogate) as a template around which monomeric complexing ligands will be polymerized. The complexing ligands will be ones containing functional groups known to form stable complexes with a specific ion and less stable complexes with other cations. Prior investigator's approaches for making templated resins for metal ions have had marginal success. We have extended and amended these methodologies in our work with Pb(II) and uranyl ion, by changing the order of the steps, by the inclusion of sonication, by using higher complex loading, and the selection of functional groups with better complexation constants. This has resulted in significant improvements to selectivity. The unusual shape of the uranyl ion suggests that this approach will result in even greater selectivities than already observed for Pb(II). Preliminary data obtained for uranyl templated polymers shows unprecedented selectivity and has resulted in the first ion selective electrode for uranyl ion.
Date: March 1, 2001
Creator: Murray, George M.; Uy, O. Manual murragm1@aplcomm.jhuapl.edu & uyom1@aplmsg.jhuapl.edu
Partner: UNT Libraries Government Documents Department

Notes and Tables for Use in the Analysis of Supersonic Flow

Description: Paper presenting a compilation of formulas, tables, and curves that have been found to be useful in the analysis of supersonic wind-tunnel data.
Date: December 1947
Creator: The Staff of the Ames 1- by 3-foot Supersonic Wind-Tunnel Section
Partner: UNT Libraries Government Documents Department

The Influence of Fold and Fracture Development on Reservoir Behavior of the Lisburne Group of Northern Alaska

Description: The Carboniferous Lisburne Group is a major carbonate reservoir unit in northern Alaska. The lisburne is detachment folded where it is exposed throughout the northeastern Brooks Range, but is relatively underformed in areas of current production in the subsurface of the North Slope. The objectives of this study are to develop a better understanding of four major aspects of the Lisburne: (1) The geometry and kinematics of detachment folds and their truncation by thrust faults, (2) The influence of folding on fracture patterns, (3) The influence of deformation on fluid flow, and (4) Lithostratigraphy and its influence on folding, faulting, fracturing, and reservoir characteristics.
Date: July 23, 2001
Creator: Wallace, Wesley K.; Hanks, Catherine L.; Whalen, Michael T.; Jensen1, Jerry; Shackleton, J. Ryan; Jadamec, Margarete A. et al.
Partner: UNT Libraries Government Documents Department

FINAL REPORT OF FY 1999, 2000, AND 2001 ACTIVITIES: CONTINUED DEVELOPMENT OF AN INTEGRATED SOUNDING SYSTEM IN SUPPORT OF THE DOE/ARM EXPERIMENTAL PROGRAM

Description: OAK B188 FINAL REPORT OF FY 1999, 2000, AND 2001 ACTIVITIES: CONTINUED DEVELOPMENT OF AN INTEGRATED SOUNDING SYSTEM IN SUPPORT OF THE DOE/ARM EXPERIMENTAL PROGRAM The basic goals of the research are to develop and test algorithms and deploy instruments that improve measurements of atmospheric quantities relevant to radiative transfer and climate research. Primary among these atmospheric variables are integrated amounts of water vapor and cloud liquid, as well as profiles of temperature, water vapor and cloud liquid. A primary thrust of this research is to combine data from instruments available to ARM to maximize their importance in radiative transfer and climate research. To gather data relevant to these studies, participation in field experiments, especially intensive operating periods, as well as the subsequent analysis and dissemination of collected data, is of primary importance. Examples of relevant experiments include several Water Vapor Intensive Operating Periods at the Southern Great Plains Cloud And Radiation Testbed site, experiments in the Tropical Western Pacific such as PROBE and Nauru'99, and experiments at the North Slope of Alaska/Adjacent Arctic Ocean site. This final report describes our analyses of data taken during these field experiments.
Date: April 30, 2002
Creator: Ed R. Westwater CIRES, University of Colorado /NOAA Environmental Technology Laboratory 325 Broadway MS R/E/ET1 Boulder, Colorado 80305
Partner: UNT Libraries Government Documents Department

Asymptotic analysis: Working Note No. 2, Approximation of integrals

Description: In this note we discuss the approximation of integrals that depend on a parameter. The basic tool is simple, namely, integration by parts. Of course, the power of the tool is evidenced in applications. The applications are many; they include Laplace integrals, generalized Laplace integrals, Fourier integrals, and Stokes' method of stationary phase for generalized Fourier integrals. These results illustrate beautifully Hardy's concept of applications of mathematics, that is, certain regions of mathematical theory in which the notation and the ideas of the (method of integration by parts] may be used systematically with a great gain in clearness and simplicity''. The notation differs slightly from Working Note No. 1, for reasons that are mainly historical. The asymptotic analysis of integrals originated in complex analysis, where the (real or complex) parameter, usually denoted by x, is usually introduced in such a way that the interesting behavior of the integrals occurs when x [yields] [infinity] in some sector of the complex plane. As there is nothing sacred about notation, and historical precedent is as good a guide as any, we follow convention and denote the parameter by x, focusing on the behavior of integrals as x [yields] [infinity] along the real axis or, if x is complex, in some sector of the complex plane. The connection with the notation of Working Note No. 1 is readily established by identifying the small parameter [epsilon] with [vert bar]x[vert bar][sup [minus]1].
Date: July 1, 1993
Creator: Garbey, M. (Lyon-1 Univ., 69 - Villeurbanne (France). Lab. d'Analyse Numerique) & Kaper, H.G. (Argonne National Lab., IL (United States))
Partner: UNT Libraries Government Documents Department

National Cost-effectiveness of ASHRAE Standard 90.1-2010 Compared to ASHRAE Standard 90.1-2007

Description: Pacific Northwest National Laboratory (PNNL) completed this project for the U.S. Department of Energy’s (DOE’s) Building Energy Codes Program (BECP). DOE’s BECP supports upgrading building energy codes and standards, and the states’ adoption, implementation, and enforcement of upgraded codes and standards. Building energy codes and standards set minimum requirements for energy-efficient design and construction for new and renovated buildings, and impact energy use and greenhouse gas emissions for the life of buildings. Continuous improvement of building energy efficiency is achieved by periodically upgrading energy codes and standards. Ensuring that changes in the code that may alter costs (for building components, initial purchase and installation, replacement, maintenance and energy) are cost-effective encourages their acceptance and implementation. ANSI/ASHRAE/IESNA Standard 90.1 is the energy standard for commercial and multi-family residential buildings over three floors.
Date: November 30, 2013
Creator: Thornton, Brian; Halverson, Mark A.; Myer, Michael; Loper, Susan A.; Richman, Eric E.; Elliott, Douglas B. et al.
Partner: UNT Libraries Government Documents Department

Flight tests of the Sikorsky HNS-1 (Army YR-4B) helicopter 2: hovering and vertical-flight performance with the original and an alternate set of main-rotor blades, including a comparison with hovering performance theory

Description: Report discussing testing of an HNS-1 (Army YR-4B) helicopter to determine the hovering data in the ground-effect region and at altitude with an original set of rotor blades and an alternate set with different aerodynamic design and surface condition.
Date: April 1945
Creator: Gustafson, F. B. & Gessow, Alfred
Partner: UNT Libraries Government Documents Department

A study of factors affecting the steady spin of an airplane

Description: Data from wind-tunnel tests on a model of the NY-1 airplane were used in a study of the effect on the steady spin of a number of factors considered to be important. The factors were of two classes, mass distribution effects and aerodynamic effects. The study indicated that mass extended along the longitudinal axis has no detrimental effect or is even slightly beneficial, mass extended along the lateral axis is detrimental if the airplane spins with the inner wing tip far down, and mass extended along the normal axis, if of considerable magnitude, has a strong favorable effect. The aerodynamic effects considered in terms of rolling, pitching, and yawing moments added to those for a conventional airplane showed that added stable rolling moment could contribute favorable effect on the spin only in decreasing the amount of inward sideslip required for equilibrium. Negative pitching moment of moderate magnitude has unfavorable effect on a high-angle-of-attack spin, and stable yawing moment has pronounced beneficial effect on the spin. Experimental data from various sources were available to verify nearly all the deductions resulting from the study of the curves. When these results were considered for the purpose of deciding upon the best means to be developed for controlling the spin, the yawing-moment equilibrium was found to offer the most promising field for research. The wing-cellule yawing moment, of which the shape of the chord-force curve is an approximate measure, should be made as small as possible in the unstable sense and the damping yawing moment of the tail should be made as large as possible. The most serious unfavorable effect on the damping yawing moment of the tail is the blanketing of the vertical surfaces by the other parts of the tail.
Date: August 1933
Creator: Scudder, Nathan F.
Partner: UNT Libraries Government Documents Department

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane Lift and Drag Characteristics of the D-558-1 and Various Wing and Tail Configurations

Description: Tests were made in the Langley 8-foot high-speed tunnel to investigate the aerodynamic characteristics of the D-558-1 airplane and various wing and tail configurations on the D-558-1 fuselage. The various wing and tail configurations were tested to determine the aerodynamic effects of aspect ratio and sweep for suitable use on the second phase of the D-558 project (D-558-2). The tests were conducted through a speed range from a Mach number of 0.40 to approximately 0.94.This part of the investigation includes the lift and drag results available for the configurations tested at this rate. The D-558-1 results indicated that the lift force break would occur at a Mach number of 0.85 with some reduction in lift at speeds above this Mach number. Tests indicated that the airplane will have satisfactory lift and drag characteristics up to and including its design Mach number of 0.85. The 35deg sweptback, 35deg swept-forward, and low-aspect-ratio (2.0) wing configurations all showed pronounced improvements in maintaining lift throughout the Mach number range tested and in increasing the critical speeds above the D-558-1 value &itical to critical Mach numbers on the order of 0.9. Insofar as lift and drag characteristics are concerned level flight at speeds approaching the velocity of sound appears practical if swept or low-aspect-ratio configurations similar to those tested are used.
Date: 1953
Creator: Wright, John B. & Loving, Donald L.
Partner: UNT Libraries Government Documents Department

ARMY GAS-COOLED REACTOR SYSTEMS PROGRAM. GCRE-I HAZARDS SUMMARY REPORT. ADDENDUM III

Description: The hazards evaluation was modified to reflect certain changes made to the equipment as a result of operating experience. These changes included: the addition of a startup interlock circuit; the modification of a startup interlock circuit; several minor modifications to the control rod actuators; and the addition of the tube-sheet cooling system. (M.C.G.)
Date: May 1, 1960
Partner: UNT Libraries Government Documents Department

Flight Test of the Lateral Stability of a 0.133-Scale Model of the Convair XFY-1 Airplane with Windmilling Propellers at Mach Numbers from 0.70 to 1.12 (TED No. NACA DE 369)

Description: A flight test of a rocket-propelled model of the Convair XFY-1 airplane was conducted to determine the lateral stability and control characteristics, The 0.133-scale model had windmilling propellers for this test, which covered a Mach number range of O.70 to 1.12. The center of gravity was located at 13.9 percent of the mean aerodynamic chord. The methods of analysis included both a solution by vector diagrams and simple one- and two-degree-of-freedom methods. The model was both statically and dynamically stable throughout the speed range of the testa The roll damping was good, and the slope of the side-force curve varied little with speed. The rudder was effective throughout the test speed range, although it was reduced to about 43 percent of its subsonic value at supersonic speeds.
Date: November 9, 1955
Creator: Hollinger, James A. & Mitcham, Grady L.
Partner: UNT Libraries Government Documents Department

Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Description: Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in smooth and rough water. The trim limits of stability, the range of stable positions of the enter of gravity for take-off, and the landing stability were determined in smooth water. The aerodynamic lift, pitching moment, and thrust were determined at speeds up to take-off speed.
Date: February 17, 1947
Creator: Havens, Robert F.
Partner: UNT Libraries Government Documents Department

Acceleration Measurements During Landings of a 1/5.5-Size Dynamic Model of the Columbia XJL-1 Amphibian in Smooth Water and in Waves: Langley Tank Model 208M, TED No. NACA 2336

Description: A 1/5.5-size powered dynamic model of the Columbia XJL-1 amphibian was landed in Langley tank no. 1 in smooth water and in oncoming waves of heights from 2.1 feet to 6.4 feet (full-size) and lengths from 50 feet to 264 feet (full-size). The motions and the vertical accelerations of the model were continuously recorded. The greatest vertical acceleration measured during the smooth-water landings was 3.1g.
Date: September 25, 1947
Creator: Clement, Eugene P. & Havens, Robert F.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane : Longitudinal Stability and Control

Description: An investigation was made of the static longitudinal stability, and control and stall characteristics of XBTK-1 dive bomber. Results indicate that the longitudinal stability will probably be satisfactory for all contemplated flight conditions at the rear-most CG location with elevator both fixed and free. Power effects were small. Sufficient elevator control will be available to trim in any flight condition above the ground. Increasing the slotted flap deflection above 30 degrees only slightly increased the max. lift coefficient.
Date: May 1945
Creator: Boykin, Rebecca I. & Weil, Joseph
Partner: UNT Libraries Government Documents Department

Measurements of the chordwise pressure distributions over the wing of the XS-1 research airplane in flight

Description: Report presenting measurements of the chordwise pressure distributions over the 8-percent-thick wing of the XS-1 research airplane at a section near the midspan of the left wing. Data are presented for a Mach number range and a normal-force coefficient of about 0.33. Results regarding the upper-surface pressure distribution, lower-surface pressure distributions, and total section loads are provided.
Date: August 4, 1948
Creator: Beeler, De E.; McLaughlin, Milton D. & Clift, Dorothy C.
Partner: UNT Libraries Government Documents Department

Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Description: From Introduction: "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."
Date: June 22, 1953
Creator: Drake, Hubert M. & Mckay, John B.
Partner: UNT Libraries Government Documents Department

The Aerodynamic Forces and Moments Exerted on a Spinning Model of the NY-1 Airplane as Measured by the Spinning Balance

Description: From Summary: "A preliminary investigation of the effects of changes in the elevator and rudder settings and of small changes in attitude upon the aerodynamic forces and moments exerted upon a spinning airplane was undertaken with the spinning balance in the 5-foot vertical tunnel of the National Advisory Committee for Aeronautics. The tests were made on a 1/12-scale model of the "NY-1" airplane. Data by which to fix the attitude, the radius of spin, and the rotational and air velocities were taken from recorded spins of the full-scale airplane."
Date: February 7, 1933
Creator: Bamber, M. J. & Zimmerman, C. H.
Partner: UNT Libraries Government Documents Department

FINAL REPORT: The Role of RUB (related to ubiquitin) Family of Proteins in the Hormone Response

Description: The Rub pathway is a conserved protein modification pathway. RUB (called Rubp1 in budding yeast, Nedd8 in animals and RUB in plants) is a ubiquitin-like 76-amino acid protein. It covalently attaches to protein using an enzymatic machinery analogous to the enzymes that attach ubiquitin to its substrate proteins. However, the nature of the complement of Rub-modified proteins in organisms was not clear. From bioinformatics analyses, one can identify a Rub activating enzymes and Rub conjugating enzymes. However, in many cases, their biochemical properties were not described. In DOE-funded work, we made major advances in our understanding of the Rub pathway in yeast and plants, work that is applicable to other organisms as well. There is a multi-subunit enzyme called SCF in all eukaryotes. The SCF consists of several subunits that serve as a scaffold (the cullin, SKP and RBX subunits) and one subunit that interacts with the substrate. This cullin protein (called Cdc53p in yeast and CULLIN 1 in plants and animals) was a known Rub target. In this work, we identified additional Rub targets in yeast as the other cullin-like proteins Cul3p and Rtt101p. Additionally we described the conservation of the Rub pathway because plant RUB1 can conjugated to yeast Cdc53p- in yeast. In the model plant Arabidopsis thaliana, we characterized the Rub activating enzymes and showed that they are not biochemically equivalent. We also showed that the Rub pathway is essential in plants and characterized plants with reduced levels of rub proteins. These plants are affected in multiple developmental processes. We discovered that they over-produce ethylene as dark-grown seedlings. We characterized a mutant allele of CULLIN1 in Arabidopsis with impaired interaction with RBX and showed that it is unstable in vivo. We used our knowledge of monitoring protein degradation to map the degradation determinants in a plant transcription ...
Date: March 27, 2013
Creator: Callis, Judy
Partner: UNT Libraries Government Documents Department

REQUEST FOR EXTENSION OF E-310

Description: No abstract prepared.
Date: January 1, 2007
Creator: Cline, D.; Cooper, P.S.; Gi1chriese, M.; Heagy, M.; Dnlay, R.; Ling, T.Y. et al.
Partner: UNT Libraries Government Documents Department

Mixture Distribution in a Single-Row Radial Engine

Description: "The distribution of the fuel among the various cylinders of a Pratt and Whitney 1340 S1H1-G engine was determined by chemically analyzing samples of exhaust gas from each cylinder. The engine was operated in the 20-foot wind tunnel at different power outputs, specific fuel consumptions, and engine speeds. The results showed that the variation in the quality of the mixture among the different cylinders was approximately 4 percent and was independent of power output, specific fuel consumption, and engine speed. The results also showed that the top cylinders operated with a lower air-fuel ratio than the bottom cylinders" (p. 1).
Date: October 1936
Creator: Gerrish, Harold C. & Voss, Fred
Partner: UNT Libraries Government Documents Department

Correlation of Buffet Boundaries Predicted From Wind-Tunnel Tests With Those Measured During Flight Tests on the F8F-1 and X-1 Airplanes -Transonic-Bump Method

Description: Memorandum presenting testing of semispan wing-fuselage models of the F8F-1 and X-1 airplanes in the 16-foot high-speed wind tunnel utilizing the transonic-bump method. The variations of lift coefficient with angle of attack and Mach number and pitching-moment coefficient with lift coefficient at various Mach numbers are presented for the models. The buffet boundaries were found to be in reasonable agreement with those determined from flight tests of full-scale airplanes.
Date: December 24, 1952
Creator: Martin, Andrew & Reed, James F.
Partner: UNT Libraries Government Documents Department

Flight measurements of the pressure distribution on the wing of the X-1 airplane (10 percent thick wing) over a chordwise station near the midspan, in level flight at Mach numbers from 0.79 to 1.00 and in a pull up at a Mach number of 0.98

Description: Report presenting measurements of chordwise pressure distribution over the 10-percent-thick wing of the X-1 research airplane at a section near the midspan of the left wing. Results regarding the upper- and lower-surface pressure distributions at a range of Mach numbers and section loads are provided.
Date: September 12, 1950
Creator: Carner, H. Arthur & Knapp, Ronald J.
Partner: UNT Libraries Government Documents Department

Lift and drag coefficients for the Bell X-1 airplane (8-percent-thick wing) in power-off transonic flight

Description: Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.
Date: June 25, 1951
Creator: Carman, L. Robert & Carden, John R.
Partner: UNT Libraries Government Documents Department