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- 100 Area process improvement program for the period November 1954--April 1955
- This is the second of a series of documents issued quarterly. The documents present, for critical examination by management and for the information of related groups, that portion of the future 100 Area technical program which relates directly and more or less immediately to the Technical-Manufacturing efforts to increase both power levels and production. An attempt is made to describe and justify the key production tests planned for the following six month period. Only those tests necessary for the relief of technical and process limitations and vital to the slug improvement program are included. Best estimates of changes in current Process Specifications during the ensuing six months are also given. To further longer range planning, power level forecasts based on foreseeable changes of technical limits and scheduled physical changes of the water plants and reactors are extended several years into the future.
- Accuracy of Volume Measurements in a Large Process Vessel
- The Non-Production Fuel Reprocessing Program involves the chemical processing of valuable reactor fuels received from privately owned power reactors. It is necessary therefore, to accurately measure the fuel material received in order to insure proper payment to reactor operator and to provide the Atomic Energy Commission with appropriate accountability data. The volume measurement study described herein was conducted in order to determine the limits of accuracy that could be obtained in measuring relatively large volumes of solution under plant processing conditions.
- Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design
- Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.
- Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
- Memorandum presenting an experimental study of the effects of several variations in configuration geometry on the aerodynamic characteristics of flat-top wing-body combinations. Generally, the configurations consist of one half of a body of revolution mounted beneath a wing of essentially arrow plan form. Results regarding the effect of trailing-edge sweep, effect of the addition of auxiliary bodies, effect of tip-flap deflection, effect of dihedral, effect of leading-edge sweep, effect of fuselage fineness ratio, effect of fuselage profile shape, and static longitudinal stability characteristics are provided.
- Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2: Pressure and force measurements at Mach numbers of 1.52 and 1.98
- Report presenting an experimental investigation of the aerodynamic characteristics of a fin-stabilized body of revolution, designated as RM-10, in a supersonic wind tunnel. Pressure distributions and force characteristics were determined at two different Mach numbers. Results regarding pressure distributions, body-alone force tests, and body-tail combination force tests are provided.
- Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds
- From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."
- Aerodynamic Loading Characteristics of a Wing-Fuselage Combination Having a Wing of 45 Degrees Sweepback Measured in the Langley 8-Foot Transonic Tunnel
- Report presenting an investigation of the aerodynamic loading characteristics of a wing-fuselage combination in the slotted test section of the transonic tunnel. The test was part of a systematic investigation of the effects of varying the amount of sweepback on wings in order to determine their suitability for transonic flight. Results regarding span load characteristics, normal-force characteristics, wing-tip angle of twist, spanwise distribution of section pitching-moment coefficient, pitching-moment characteristics, and fuselage characteristics in presence of wing are provided.
- Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow
- From Introduction: "This report is concerned with the derivation of expressions for the velocity potential and associated forces and moments for oscillating triangular wings in supersonic flow. The purpose of the present report is to make use of the expanded form of the velocity potential to obtain the forces and moments, based on the first terms of this potential, for a rigid triangular wing performing vertical and pitching sinusoidal oscillations in mixed supersonic flow."
- Aircraft Reactor Test Hazards Summary Report
- The successful completion of a program of experiments, including the Aircraft Reactor Experiment (ARE), has demonstrated the high probability of producing militarily useful aircraft nuclear power plants employing reflector-moderated circulating-fuel reactors. Consequently, and accelerated program culminating in operation of the Aircraft Reactor Test (ART) is under way. In order to adhere to the compressed schedule of the accelerated program, it is essential that the Atomic Energy Commission approve the 7500 Area in Oak Ridge as the test site by February15, 1955. This report summarizes the hazards associated with operating the contained 60-Mv reactor of the ART at the proposed Oak Ridge test site.
- Alloys of Uranium with Zirconium, Chromium, Columbium, Vanadium, and Molybdenum
- Abstract: Information on five uranium binary alloy systems has been surveyed. These systems are the alloys of uranium with zirconium, chromium, columbium, vanadium, and molybdenum. The equilibrium diagrams are discussed, and where available, data have been included on diffusion studies, cladding experiments, and mechanical properties.
- Alloys of Uranium With Zirconium, Chromium, Columbium Vanadium, and Molybdenum
- No Description Available.
- Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
- From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
- Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine
- From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."
- An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability
- From Introduction: "The purpose of the present study is to investigate these suggested methods for reducing the undesirable pitching and yawing motions of an airplane during roll maneuvers. The airplane characteristics used in this study were those of the F-100A airplane having the original small vertical tail as shown in figure 1."
- An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
- Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
- An analysis of axial- and centrifugal-flow turbojet-engine performance with variable-area exhaust nozzle
- From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."
- Analysis of experimental low-speed loss and stall characteristics of two-dimensional compressor blade cascades
- From Introduction: "In the present report, the concept of velocity diffusion is applied in an analysis of blade losses expressed in terms of the fundamental parameter of wake momentum thickness. Restrictions and limitations involved in the application of the results to cascade performance analyses are discussed."
- Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers
- Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.
- An Analysis of the Effects of Aeroelasticity on Static Longitudinal Stability and Control of a Swept-Wing Airplane
- From Introduction: "The results of the aforementioned study are presented in this report together with the method of analysis employed. The net stability change is shown together with the individual contributions due to flexibility of wing, tail, and fuselage, both including and neglecting the effect of inertial loads."
- Analysis of the Liquid-Metal Turbojet Cycle for Propulsion of Nuclear Powered Aircraft
- From Introduction: "The present report gives an analysis of the design point performance of nuclear powered liquid-metal turbojet engines. The effect of varying the assumptions necessary to calculate gross weight and reactor heat release from engine data is presented."
- Analysis of the Liquid-metal Turbojet Cycle for Propulsion of Nuclear Powered Aircraft
- Report presenting an analysis of the nuclear powered liquid-metal turbojet cycle for a wide range of engine operating conditions at a range of flight Mach numbers and altitudes. The method of analysis and working charts are presented to facilitate investigations beyond the scope of this report.
- Analysis of the Sodium and Water Performance of the Atwood-Morrill Swing Check Valve
- This report addresses the analysis of the sodium and water performance of the Atwood-Morrill swing check valve.
- Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 2: air-cooling systems
- Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade air- and liquid-cooling systems for turbojet application in guided missiles and supersonic interceptor aircraft. Results regarding the coolant passage heat-transfer-coefficients, nonrefrigerated air-cooling-system characteristics, and refrigerated-air-cooling-system characteristics are provided.
- AN APPLICATION OF GAME THEORY TO SPECIAL WEAPONS EVALUATION
- A metbed was introduced for combining the techniues of classical Lanchester theory of combat with those of game theory toward the end of selecting optimal strategies in combat with special weapons. In the application of this method to the example in which only the defender had atomic weapons,. it was showm that the attacker always chose either to disperse his troops the maximum amount or not to disperse his troops at all. The defender always chose to employ a mixed strategy consisting of the weapon systems of either two intermediate weapons or four small weapons. If both the defender amd attacker hnd access to atomic weapons, then the opticmal strategy for the attacker was to employ the weapon system consisting of four small weapons and to use a mixed stratregy for the dispersion of his troops. On the other hand, the defender never dispersed his troops amd always used a mixed strategy for tee - weapon systems. In the example where the defender has a fixed weapon system and chooses to optimize his aiming procedure, it was shown that the optimal aiming procedure does not involve only the aimimg procedures which are optimal against each of the fixed dispersion patterns for the attacker. The model discussed in this paper is far from realistic, but the authors feel that certain interesting trends may be obtained by such elementary discussions. Two ways in which to approach more reslism are to introduce into the combat the time at which the different groups become engaged amd to obtain a more realistic model for the basic group. (auth)
- APPLICATIONS OF MONTE CARLO
- No Description Available.
- APPR critical experiment program meeting
- This report addresses the APPR critical experiment program meeting.
- Attritioning of Temple Mountain Ore
- Abstract: The results of both dry and wet attritioning of Temple Mountain ore are presented. In order to obtain effective attritioning on this ore, the amphaltite must be removed before attritioning. With the asphaltite present, dry attritioning causes a build-up of asphaltite on the surface of sand grains, with consequent loss of uranium values. In wet attritioning, the asphaltite is not broken down or attritioned, because of its low specific gravity and resilience.
- Bibliography of NACA Reports Related to Aircraft Control and Guidance Systems January 1949 - April 1954
- This report lists pertinent NACA papers presenting research results which have a direct bearing on control system design and performance for both piloted and automatically controlled aircraft. Limited reference is also made to NACA reports on aircraft engine controls and to research techniques and instrumentation pertinent to the study of control systems and aircraft dynamics in flight. Reports published between January 1949 and April 1954 are listed in chronological order and cross referenced.
- Blow-out velocities of various petroleum, slurry, and hydride fuels in a 1 7/8-inch diameter combustor
- Report presenting testing using a 1 7/8-inch inside-diameter combustor that can measure and compare the blow-out velocities of single-component fuels, slurries, and fuel mixtures with a wide range of reactivity and physical properties. The blow-out velocities of isooctane, n-heptane, isopentane, allyl chloride, and propylene oxide varied int he same way as flame speeds of the fuels. Results regarding the effects of different additives are also provided.
- Calculation of Aerodynamic Forces on an Inclined Dual-Rotating Propeller
- Report presenting a method for calculating the aerodynamic forces on the blades of a dual-rotating propeller with its thrust axis inclined to the air stream. Comparison of the fluctuating aerodynamic forces due to pitched or yawed operation of a dual-rotating propeller show that the fluctuation in forces on the front component tend to be greater than those on the rear component.
- CALCULATION OF THE VOLUME OF LIQUID CONTAINED IN A PARTIALLY-FILLED RIGHT CIRCULAR CYLINDER INCLINED TO THE HORIZONTAL
- No Description Available.
- CALCULATION OF WALL-SCATTERED GAMMA RADIATION ESCAPING THROUGH A SHIELD OPENING--APPLICATION TO THE HRT
- No Description Available.
- Calculation of Wall-Scattered Gamma Radiation Escaping through a Shield Opening - Application to the HRT
- A simplified method was developed for calculating wall-scatter gamma radiation escaping through a shield opening. The method was applied to the HRT and the results showed that next to the line of sight contribution, scattering of the wall of the shield opening was the main contribution to the dose at the rear edge of the shield. Design charts were prepared that give the dose as a function of the gamma source location with the reactor cell.
- Casting of Blanket Bricks, Ring, Plug, and Control Rods for the Experimental Breeder Reactor (CP-4)
- The cup assembly of the Experimental Breeder Reactor (EBR) consists of blanket bricks, inner rings, and safety plug, all of natural uranium. The design of the finish machined brick is shown in Figure 1. These pie shaped bricks when stacked together, 12 bricks arranged in circular form and stacked seven rings high, comprise the cylindrical portion of the outer blanket, 17.875" I.D. x 30.875" O.D. after machining and canning. The inner ring, which is shown in Figure 2, fits inside the bottom layer of bricks. The circular opening in the center of the inner ring is closed by the safety plug shown in Figure 3.
- Causes of damage to tube 1794-C
- Tube 1794-C was removed from the pile as a leaker on July 15, 1954. The tube had been in-pile since startup and had contained a charge of 32 ``C`` metal slugs just prior to discharge. The tube was slit and examined at the 105-DR underwater viewing facility by Pile Coolant Studies tube examination personnel. A report is made of the examination of tube 1794-C which revealed areas of severe pitting damage. This damage was apparently caused by cocked slugs abrading the tube. The attack was great enough to cause perforation of the tube at about 27 feet from the rear Van Stone flange. Examination of the slugs showed that a considerable number had been cocked. Evidence of severe tube scarring and rib grooves was found on the slugs. Strikingly similar examples of pitting and grooving were observed on flow laboratory minitubes and slugs exposed in high velocity water. It is concluded that the damage observed both in- and ex- pile was caused by the chattering of misaligned low density slugs in a high velocity stream. If the number of in-pile occurrences of this attack becomes excessive it is recommended that the water flow rate in tubes containing ``C`` metal slugs be maintained as low as is practical and consistent with corrosion limitations.
- Cell Removal Program (704 Program Delta). Job No. 51338
- No Description Available.
- Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85
- Report presenting an experimental study of the compression fields around axially symmetric isentropic spikes with varying degrees of compressive flow turning made at a Mach number of 3.85 to analyze the basic shock structures and thereby establish further design criteria for supersonic-inlet applications. Results regarding the original isentropic spike and cowl, isentropic survey-spike configurations, and external-compression limitations are provided.
- Chemical Processing Department Daily Production Reports, October 1, 1958--December 31, 1958
- This report presents the daily production data for the redox process, purex process, and uranium trioxide operations at the Hanford Engineer Works for November 1, 1958 to December 31, 1958. (JL)
- Chemical Technology Division Unit Operations Section Monthly Progress Report, October 1958
- Tungsten and graphite are unsuitable materials of construction for a UF/ sub 6/ inlet nozzle in a continuous DRUHM reactor. Preparation of feed was completed for an extended Fluorox test. Difficulties were experienced in the operation of a fluidized bed TbNT denitrator. Flame denitration of UNH and TbNO produced mixed oxides of 1 to 14 micron mean particle size. The chloride capacity of Dowex 21K was measured, and equilibria measurements of uranium sorption from sulfate solutions were continued. Siliceous deposits in the stripping column caused the termination of a Darex run with a prototype APPR fuel element. Hot runs were begun on the chemical dejacketing of irradiated PWR blanket pins. The addition of formaldehyde to neutralize "25" waste reduced the recovery of nitrate from the calciner off-gas from 76% to 23%. (For preceding report see CF-58-9-62.) (auth)
- Chemistry Division, Section C-II, Summary Report For April, May, And June 1952
- This report was written by different scientist on various experiments of solid state, physical chemistry, radiochemistry and analytical, and special problems.
- Comparative Study of Turbofan and Turbojet Engines
- Report presents a comparison of turbofan and turbojet engines for Mach numbers of up to 3.0 and conventional hydrocarbon fuels. There are four parts of the report: a cycle analysis of turbofan engines and information about their designs, a comparison of several commercial engines proposed for the Air Force, component performance and development problems for turbofan and turbojet engines, and a summary and conclusions based on mission studies.
- Comparison at supersonic speeds of translating spike inlets having blunt- and sharp-lip cowls
- Report presenting an investigation of two translating spike inlets with blunt- and sharp-lip cowls in the supersonic wind tunnel at a range of free-stream Mach numbers and angles of attack. Results regarding the inlet stability, critical inlet performance at zero angle of attack, and inlet-engine matching are provided.
- A comparison of carrier approach speeds as determined from flight tests and from pilot-operated simulator studies
- Report presenting a simplified analog simulator that can be used to predict the minimum comfortable approach speeds that could be used in carrier landings for airplanes that are limited by their ability to control altitude. Predicted speeds from initial tests on several planes are compared with values from flight tests in order to indicate the validity of simulator results.
- Comparison of experimental and theoretical normal-force distributions (including Reynolds number effects) on an ogive-cylinder body at Mach number 1.98
- Report presenting normal-force and pressure distributions for a body of revolution consisting of a fineness-ratio-3, circular-arc, ogival nose tangent to a cylindrical afterbody 7 diameters long. Comparisons of theoretical and experimental distributions indicate that available theoretical methods are only accurate for angles of attack up to about 5 degrees.
- A Comparison of Flight Measurements With Calculations of the Horizontal-Tail Root Bending Moments for a Jet-Powered Bomber Airplane
- Memorandum presenting a comparison made between the incremental aerodynamic root bending moments on the horizontal tail of a jet-powered bomber airplane measured during a flight investigation over a range of Mach numbers and the bending moments calculated by using available theoretical models in conjunction with measured loads, elevator positions, and elevator and stabilizer twists. Results regarding abrupt maneuvers, gradual turn maneuvers, and effects of downwash are provided.
- Comparison of the Combustion Performance of Shell UMF, Grade C, MIL-F-5624C, Grade JP-5, Fuels in a Heavy-Duty XRJ47-W-9 Ram-Jet Engine
- Comparable combustion performance data for Shell UMF, grade C, and MIL-F-5624C, grade JP-5, fuels were obtained using a heavy-duty version of the XRJ47-W-9 ram-jet engine operated in a 2.75 Mach number free-jet facility. Data were obtained for the two fuels over a range of fuel-air ratios, engine airflows, and engine-inlet temperatures. The test conditions were selected to provide combustor-inlet temperatures. The test conditions were selected to provide combustor-inlet conditions approximately representative of those which would be encountered over a range of altitudes and flight Mach numbers. The variation of combustion efficiency with fuel-air ratio for the two fuels is compared at the several inlet conditions. The pilot-burner ignition and operating limits with both fuels are also included. In general, the combustion efficiency with Shell UMF, grade C, fuel was 1 to 4 points lower than with MIL-F-5624C, grade JP-5, fuel.
- Comparisons of the Effectiveness and Hinge Moments of All-Movable Delta and Flap-Type Controls on Various Wings
- A comparative evaluation was made for all-movable delta and flap-type controls on several wing plan forms. Comparison of these experimental results from various test facilities shows the effectiveness on various wing plan forms and an evaluation of hinge-moment characteristics of all-movable delta controls, swept trailing-edge flap, and straight trailing-edge flap-type controls.
- Compatibility of Pentaborane With Materials Used for Seals, Gaskets, and Construction
- Memorandum presenting the compatibility of pentaborane with aluminum foil, 24S-T and 17S-T aluminum, and 50-50 tin-lead solder in the range of -30 to -50 degrees F for 7 hours, at 90 degrees F for 6.5 hours, and at 70 degrees F for 28 days. Results were evaluated by determination of the loss in weight after the test period, metallographic inspection, and comparison with blanks carried through test conditions without exposure to the liquid. The evaluation of results was made by visual inspection and physical tests of dimensional stability, tensile strength, elasticity, and gain or loss of weight.
- Conference on "Hot" Laboratory Design Held at Brookhaven National Laboratory on September 19, 1947
- From introduction: "This conference represents the first attempt by a project-wide group of scientists and engineers to collaborate on the problem associated with the planning and design of "Hot" Laboratories. The idea, as originally conceived by Dr. W. E. Winsche, was to discuss some general and perhaps some specific aspects of "Hot" Laboratory design with a small group of interests individuals from various sites."
- Construction status report - 100-C for week ending - January 18, 1955
- No Description Available.