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Coupled Hydrodynamic-Structural Response Analysis of Piping Systems
This report describes in detail the expansion of the ICEPEL code for the coupled hydrodynamic-structural response analysis of pipe-elbow loops to general piping systems. A generalized piping-component model, a branching tce junction, and a surge-tank model are introduced and coupled with the pipe-elbow loop model so that a general piping system under the effect of internally traveling pressure pulses can be analyzed hydrodynamically, as well as structurally.
ICEPEL Analysis of and Comparison with Simple Elastic-Plastic Piping Experiments
The results of simple elastic-plastic piping experiments for straight pipes and single-elbow loop systems are interpreted and evaluated. The experiments are also analyzed by the ICEPEL piping code, and the analytical results are compared against the experimental data.
The A.B.C. "Robin" (British): A Single-Seat Cabin Monoplane
Report discussing the A.B.C. Motors Robin, a single-seat monoplane that was built for pilot comfort, speed, and fuel efficiency. Information about the structural design, dimensions, weight, performance, and rough blueprints is included.
Design of a Precast Concrete Stay-in-Place Forming System for Lock Wall Rehabilitation
Report describing the design of forming a system to use pre-cast concrete for rehabilitating damaged walls in locks, as a way to prevent problems with cracking in replacement air-entrained concrete used in standard methods.
Feasibility Study, Optimum Natural Uranium, Gas Cooled, Graphite Moderated Nuclear Power Plant for United States Atomic Energy Commission, Idaho Operations Office
Report containing "a discussion of the feasibility design and cost estimates for a gas cooled, natural uranium, graphite moderated power plant optimized for minimum power cost" (p. 3).
Feasibility Study, Optimum Partially Enriched Uranium, Gas Cooled, Graphite Moderated for United States Atomic Energy Commission, Idaho Operations Office
Report that contains "a preliminary design and feasibility studies of gas cooled, graphite moderated, nuclear power plants" (p. 1).
Savannah River Project Site Report: 30,000 KW Prototype Partically Enriched Uranium Gas Cooled, Graphite Moderated Nuclear Power Plant for United States Atomic Energy Commission Idaho Operations Office
Report describing a modified prototype of a nuclear reactor that uses partially uranium-enriched fuel and is cooled by helium. The construction site, site safety aspects, and design and construction costs are included.
Conceptual Design of a Rapid-Cycling Synchrotron for the KFA-Juelich Spallation Neutron Source
An accelerator group was established at ANL by the request of KFA-Juelich to carry out a conceptual design study and cost estimate for a rapid-cycling synchrotron as a possible first stage program on spallation neutron sources at KFA-Juelich. This set of notes is the individual notes which form the basis of the final report under this proposal prepared in January 1983. This document contains 37 papers/notes for Advanced Accelerator Development - Neutron Source Series Notes...numbered AAD-N-1 through AAD-N-37. Each note or paper is written by various authors.
Accelerator Beam Pulsing System With Extremely Wide Range of Pulse Lengths and Pulse Repetition Rates
The following document describes the usage and results of sending pulsed beams of electrically charged particles with electrically wide range of pulse lengths and pulse repetition rates.
Uranium Hydrogeochemical and Stream Sediment Reconnaissance in Lincoln and Flathead Counties, Northwest Montana
From abstract: Between mid-May and late June 1976, 3409 water and water-transported sediment samples were collected from 1781 locations spread over an approximate 17 000 kilometer area of northwestern Montana. All of the samples were analyzed for total uranium at the LASL, using standardized procedures and rigorous quality controls--the waters by fluorometry and the sediment (and those waters with >10 parts per billion uranium) by delayed-neutron counting methods.
Uranium Hydrogeochemical and Stream Sediment Reconnaissance Data from the Area of the Noatak and Portions of the Baird Mountains and Ambler River Quadrangles, Alaska
From introduction: This report describes work done in the Noatak and portions of the Baird Mountains and Ambler River, Alaska, National Topographic Map Series (NTMS) quadrangles (1:250 000 scale) by the Los Alamos Scientific Laboratory (LASL) as part of the nationwide Hydrogeochemical and Stream Sediment Reconnaissance (HSSR).
Uranium Hydrogeochemical and Stream Sediment Reconnaissance of the McGrath and Talkeetna NTMS Quadrangles, Alaska, Including Concentrations of Forty-Three Additional Elements
From abstract: During the summer of 1977, 1268 water and 1206 sediment samples were collected from 1292 lakes and streams throughout the 33 600-km2 area within the boundaries of the McGrath and Talkeetna National Topographic Map Series quadrangles in south-central Alaska. Each of the water samples was analyzed for uranium and 12 other elements, and each of the sediment samples was analyzed for uranium, thorium, and 41 other elements. All of the field and analytical data are listed in appendixes to this report, but only the uranium and thorium data are discussed herein.
Economic Evaluation of a 300 Mwe Fast Supercritical Pressure Power Reactor
Report regarding Hanford Laboratories' 300 Mwe fast supercritical pressure power reactor. This includes descriptions of the plant and reactor, their operations, safety systems, and plant economics. Appendices begin on page 107.
Transportation of Iron Ore, Limestone, and Bituminous Coal on the Great Lakes Waterway System: With Projections to 1995
Report issued by the U.S. Bureau of Mines discussing the transportation of minerals on the Great Lakes Waterway System. As stated in the abstract, "this study provides data on the physical and hydrological makeup of the Great Lakes waterway system and forecasts quantities, traffic patterns, and shipping cost of prospective bulk mineral commerce projected to be transported upon it" (p. 1). This report includes maps, tables, and illustrations.
Optical Mapping of Oak Ridge Research Reactor Experiment Tubes
Report issued by the Oak Ridge National Laboratory discussing optical mapping of experiment tubes. Descriptions of experiment equipment, and designs of the tubes are presented. This report includes tables, illustrations, and photographs.
Aircraft Reactor Test Removal and Disassembly
Report documenting the dissection of a reactor called the Aircraft Reactor Test (ART). Includes the removal of the reactor from its test cell, component removal, and plans for a for a disassembly building facility.
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section
Report presenting tests in the two-dimensional low-turbulence pressure tunnel to study the interference effects of various pusher-propeller shaft-housing combinations on a low-drag airfoil. Thirty different combinations were tested, variations being made in shaft size, shape, angle, and fillet.
The Effects of Roughness at High Reynolds Numbers on the Lift and Drag Characteristics of Three Thick Airfoils
"In connection with studies of airfoils applicable to large high-speed aircraft, the effects of roughness on three 22-percent-thick airfoils were investigated. The tests were made over a range of Reynolds number from about 6 to 26 x 10(exp 6) for the airfoils smooth and with roughness strips applied to the surfaces. The results indicated that for the roughened models the scale effect was generally favorable" (p. 1).
Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons
Report presenting the results of flight investigations showing that a beveled trailing-edge aileron gives as low or a lower profile drag than a contour aileron. Section profile drag and lift coefficients with two different types of ailerons were obtained at 3 different Reynolds numbers.
Airship Model Tests in the Variable Density Wind Tunnel
This report presents the results of wind tunnel tests conducted to determine the aerodynamic characteristics of airship models. Eight Goodyear-Zeppelin airship models were tested in the original closed-throat tunnel. After the tunnel was rebuilt with an open throat a new model was tested, and one of the Goodyear-Zeppelin models was retested. The results indicate that much may be done to determine the drag of airships from evaluations of the pressure and skin-frictional drags on models tested at large Reynolds number.
The drag of two streamline bodies as affected by protuberances and appendages
This report presents the results of wind tunnel tests of two airship models conducted to determine the drag coefficients at zero pitch, and the effect of fins and cars and of flat and streamlined protuberances located at various positions along the hull. During the investigation the stern of one model was rounded off to produce a blunter shape. The extreme range of the Reynolds number based on the over-all length of the models was from 1,300,000 to 33,000,000. At large values of the Reynolds number the streamlined protuberance affected the drag very little, and the additional drag caused by the flat protuberance was less than the calculated drag by the protuberance alone. The fins and cars together increased the bare-hull drag about 20 per cent.
Experiments With an Airfoil Model on Which the Boundary Layers Are Controlled Without the Use of Supplementary Equipment
This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.
Fuselage-drag tests in the variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5
From Summary: "Results are presented of the drag tests of six bodies of revolution with systematically varying shapes and with a fineness ratio of 5. The forms were derived from source-sink distributions, and formulas are presented for the calculation of the pressure distribution of the forms. The tests were made in the N.A.C.A. variable-density tunnel over a range of values of Reynolds number from about 1,500,000 to 25,000,000. The results show that the bodies with the sharper noses and tails have the lowest drag coefficients, even when the drag coefficients are based on the two-thirds power of the volume. The data shows the most important single characteristic of the body form to be the tail angle, which must be fine to obtain low drag."
Interference effects of longitudinal flat plates on low-drag airfoils
Three airfoils were tested with an intersecting flat plate normal to the span as a preliminary study of interference effects on airfoils. Small interference effects were noted on the first two airfoils, while larger effects were noted on the NACA 66,2-422 section, which had previously been shown to be unconservative with respect to separation. Airfoils known to be conservative should be used for inboard sections subject to nacelle and fuselage interference.
Lift and Drag Characteristics of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation
Report presenting a wooden model equipped with a slotted flap that was tested in the two-dimensional tunnel. It represented a wing section of the Curtiss-Wright P-60A airplane and the NACA 66,2-118 section. Results regarding lift characteristics, drag coefficients, and flap deflection characteristics are provided.
Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation
"Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane
Report presenting pressure distribution measurements on two 24-inch chord models equipped with Fowler flaps in the two-dimensional low-turbulence pressure tunnel. Results regarding pressure-distribution diagrams and normal-force and moment coefficients are provided.
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
Report presenting testing in the two-dimensional tunnel of four models submitted by the Glenn L. Martin Company as intermediate sections of the wing of the XB-33 airplane. Each airfoil model had different types of flaps or no flaps at all. Results regarding the lift and drag data, lift coefficients, effect of flap positions, aileron effects, drag coefficients, and hinge-moment coefficients are provided.
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps
From Summary: "Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients."
Tests of a Highly Cambered Low-Drag-Airfoil Section with a Lift-Control Flap, Special Report
Tests were made in the NACA two-dimensional low turbulence pressure tunnel of a highly cambered low-drag airfoil (NACA 65,3-618) with a plain flap designed for lift control. The results indicate that such a combination offers attractive possibilities for obtaining low profile-drag coefficients over a wide range of lift coefficients without large reductions of critical speed.
Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the NACA variable-density tunnel
From Summary: "A preliminary investigation of the stalling processes of four typical airfoil sections was made over the critical range of the Reynolds Number. Motion pictures were taken of the movements of small silk tufts on the airfoil surface as the angle of attack increased through a range of angles including the stall. The boundary-layer flow also at certain angles of attack was indicated by the patterns formed by a suspension of lampblack in oil brushed onto the airfoil surface. These observations were analyzed together with corresponding force-test measurements to derive a picture of the stalling processes of airfoils."
Lift and Drag Tests of Three Airfoil Models With Fowler Flaps Submitted by Consolidated Aircraft Corporation
Report presenting lift and drag tests made in the two-dimensional tunnel of three airfoil models. The models represented intermediate sections on alternative wings of the XB-32 airplane and were equipped with 0.30 Fowler flaps. Results regarding the Davis model, the C.A.C. model, and low-drag model are provided.
Summary of Airfoil Data
From Summary: "The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application."
Tail Buffeting
"An approximate theory of buffeting is here presented, based on the assumption of harmonic disturbing forces. Two cases of buffeting are considered: namely, for a tail angle of attack greater and less than the stalling angle, respectively. On the basis of the tests conducted and the results of foreign investigators, a general analysis is given of the nature of the forced vibrations the possible load limits on the tail, and the methods of elimination of buffeting" (p. 1).
The Theory and Operation of Shock-Load Ferroelectric Transducers
A report discussing "an explosive ferroelectric power supply and the experimental approach followed in determining its operating characteristics."
The Neutron Sensitive PCP Ionization Chamber
Manual of operation for a neutron sensitive ionization chamber for reactor instrumentation.
Interim Report on the Location of Nonsaline Uraniferous Waters Suitable for Ion-Exchange Process
From introduction: The Trace Elements Section Washington Laboratory had developed the methods used in anticipation of handling an increased volume of water analyses as this preliminary project is expanded into a full-scale investigation. The efforts of these groups were coordinated by the Trace Elements Planning and Coordination Office.
A Low Cost Experimental Neutron Chain Reactor Part 2
Description of cooling, shielding, controls are discussed for 100 kw and 1 Mw operation of a low cost experimental neutron chain reactor.
Divide Cut Drainage Structures Tennessee-Tombigbee Waterway Mississippi and Alabama: Hydraulic Model Investigation
Report on model tests related to drainage structures for the Tennessee-Tombigbee Waterway to provide recommendations about construction.
Modifications to Filling and Emptying System of Lock No. 1, Mississippi River, Minneapolis, Minnesota =: Hydraulic Model Investigation
From abstract: The existing locks at Locks and Dam No. 1 were constructed between 1929 and 1932. Problems have been experienced with accumulation of ice and debris at the intakes, air entrapment in the culverts of the filling and emptying system, excessive turbulence in the lock chamber during filling, and hazardous conditions downstream from the locks during emptying operations.
Filling and Emptying System, Cannelton Main Lock, Ohio River, and Generalized Tests of Sidewall Port Systems for 110- by 1200-ft Locks: Hydraulic Model Investigation
Report providing the results of a hydraulic model investigation of the Cannelton Lock proposed for construction on the Ohio River. It includes detailed information about the tests and suggested dimensions and features of the final lock.
Filling and Emptying System, Dardanelle Lock, Arkansas River: Hydraulic Model Investigation
Report on investigations into the construction of a lock in the Arkansas River including results of model tests and recommendations.
Filling and Emptying Systems, Low-Lift Locks, Arkansas River Project: Hydraulic Model Investigation
Results of a hydraulic model investigation based on locks in the Arkansas River before the construction of additional locks. "Model studies of the filling and emptying system proposed for use at the low-lift locks in the Arkansas project were conducted to confirm the adequacy of the original design hydraulic system, and to develop, if needed, improvements in the system" (p. 2).
Filling and Emptying Systems, Millers Ferry and Jones Bluff Locks, Alabama River, Alabama: Hydraulic Model Investigation
Report providing results of hydrualic model investigations to test a new type of lock filling and emptying system to determine the final suggested construction for the Millers Ferry Lock in the Alabama River.
Reaction of Glass During Gamma Irradiation in a Saturated Tuff Environment, Part 3: Long-Term Experiments at 1x10^4 Rad/Hour
Report on experiments to assess the importance of radiation effects on waste glass corrosion. This third part contains a description of the experiments, results, and discussion, with conclusions and related appendices.
The Theory of a Free Jet of a Compressible Gas
"In the present report the theory of free turbulence propagation and the boundary layer theory are developed for a plane-parallel free stream of a compressible fluid. In constructing the theory use was made of the turbulence hypothesis by Taylor (transport of vorticity) which gives best agreement with test results for problems involving heat transfer in free jets" (p. 1).
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response
Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the speed of response, effect of Mach number on response, and effect of networks are provided.
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-Effect of Method of Positioning the Radar Antenna on the Speed of Response
Memorandum presenting a linear theoretical analysis of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. It is shown that, with the antenna stabilized in space, the effect of component lags on the response is small, so that the speed of response is small, so that the speed of response can be made to approach closely that of the airframe alone.
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Missile Configuration on the Speed of Response
Memorandum presenting a comparison of the maximum speed of response that can be attained by three missile configurations, a variable-incidence-wing, a canard, and a tail-control, in combination with a particular proportional navigation guidance system. The configuration that allows the most rapid overall guidance-system response depends on the control-system characteristics. Results regarding the rate-only feedback and rate and normal acceleration feedback are provided.