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Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge
A preliminary theoretical and experimental investigation has been made on the aerodynamic characteristics of blunt-trailing-edge airfoils at supersonic velocities. The theoretical considerations indicate that properly designed airfoils with moderately blunt trailing edges can have less profile drag, greater lift-curve slope, and high maximum lift-drag ratio than conventional sections. These predictions have been substantiated by experimental measurements on airfoils of 10-percent-thickness ratio at Mach numbers of 1.5 and 2.0, and at Reynolds numbers between 0.2 and 1.2 million.
Response of Homogeneous and Two-Material Laminated Cylinders to Sinusoidal Environmental Temperature Change, With Applications to Hot-Wire Anemometry and Thermocouple Pyrometry
Note presenting an investigation of the problem of the responses of homogeneous and two-material laminated cylinders to sinusoidal environmental temperature changes. The results are applicable to situations in which small heat-transfer coefficient changes occur in the absence or presence of environmental temperature changes.
Selected Annotated Bibliography of the Geology of Uraniferous Phosphorites in the United States
From Introduction: "The references in this bibliography represent nearly all of the reports pertaining to uranium in domestic phosphorites that were publicly available as of May 31, 1955."
Separation of Aluminum Phosphate Minerals From Kaolinite by Selective Solution
Abstract: Wavellite, crandallite, and millisite are completely dissolved by boiling samples for 20 minutes with 1+1 hydrochloric acid; only 1 percent of the aluminum present in kaolinite is dissolved. This method of decomposition can therefore be used for differentiating the aluminum present in wavellite, crandallite, and millisite form that in kaolinite in samples from the aluminum phosphate zone. This method should prove valuable in prospecting and benefication studies.
The Spectrophotometric Determination of Vanadium as Thiocyanate in Acetone-Water Medium
A report about a method for the spectrophotometric determination of vanadium in acetone-water medium based on the reaction between vanadium (IV) and thiocyanate.
Theory of Dynamic Creep
An analysis is given of the causes of the increase in the creep of a material under dynamic loads. A theory of dynamic creep is proposed based on the after-effect theory of Becker. Three circumstances that must be taken into account when theoretically treating dynamic creep are provided.
The Thoron-Tartaric Acid Systems for the Spectrophotometric Determination of Thorium
A report about thoron which is popularly used for the spectrophotometric determinations of thorium. The study describes the use of tartaric acid as a masking reagent for zirconium.
Uraniferous Magnetite-Hematite Deposit at the Prince Mine, Lincoln County, New Mexico
A report about a prometasomatic magnetite-hematite deposit in Permian sedimentary rocks near the margin of the Lone Mountain stock in Lincoln County, New Mexico, contains between 0.015 percent and 0.031 percent uranium.
Uranium Deposits of the Northern Part of the Boulder Batholith, Montana
From abstract: Uranium minerals and radioactivity anomalies occur in many silver lead veins and chalcedony veins and vein zones in the Boulder batholith of southwestern Montana.
Variation of boundary-layer transition with heat transfer on two bodies of revolution at a Mach number of 3.12
Report presenting an investigation at Mach number 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained from a cone cylinder and a parabolic-nosed cylinder at a range of Reynolds numbers based on body length. Results regarding the effect on transition of surface cooling, cold-wall data, and turbulent flow are provided.
Visualization study of secondary flows in turbine rotor tip regions
Report presenting a visualization study using smoke to see the secondary-flow phenomena in the rotor-blade tip region of a low-speed turbine. Measurements of the factors affecting the flow patterns were recorded from visual observations. Results regarding a general description of the smoke patterns, shroud boundary-layer considerations, transition rotor tip speed, and high-speed-turbine operating conditions are provided.
Wind-tunnel investigation at low speed of effect of size and position of closed air ducts on static longitudinal and static lateral stability characteristics of unswept-midwing models having wings of aspect ratio 2, 4, and 6
Report presenting an investigation at Mach number 0.13 in the stability tunnel to determine the effects of closed wing-root air ducts on the static longitudinal and lateral stability characteristics of unswept-midwing models with wings of aspect ratio 2, 4, and 6.
Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane
Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
X-Ray Diffractometer Studies of Some Vanadium Silicates
Report discussing a study in which a group of claylike silicates containing vanadium were examined by X-ray diffraction methods to determine their mineralogic composition.
Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test
Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting
From Summary: "The dynamic characteristics of an airplane with a proportional-gain roll-control autopilot are discussed. A comparison of three different high-speed fighter airplanes is presented. The dynamic effects of time lags and various gains in the system are described."
Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6
Report presenting a collection and summary of the wing-aileron rolling-effectiveness data obtained as part of an investigation of lateral control using rocket-powered test vehicles in free flight over a range of Mach numbers. Some effects of trailing-edge angle, aileron-chord ratio, aileron span and location, aspect ratio, wing sweepback, and wing-tail interference are provided.
Design Notes and Component Recommendations for Gamma-Scintillation Monitoring Systems
The design notes contained herein may assist in preliminary studies concerning feasibility of any proposed gamma monitor system. The minimum and maximum solution concentrations for each type of system are listed. The data is based on 32 ml liquid sample.
A limited analysis of buffeting experienced in flight by a North American F-86A-1 airplane with and without large external fuel tanks
Report presenting a limited analysis of data collected during buffeting of a North American F-86A-1 airplane with and without large external fuel tanks installed in order to explore the buffeting characteristics of the different configurations. A two-part analysis was carried out to determine the effect of the tanks on the general buffeting characteristics and to make a detailed study of the electrical and numerical frequency analysis techniques of one run.
Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2
Report discussing testing of the effects of aeroelasticity on the rolling effectiveness on a model of a McDonnell F-101A airplane wing. The aeroelastic losses varied based on the Mach number and altitude.
Theoretical investigation of the effects of configuration changes on the center of pressure shift of a body-wing-tail combination due to angle of attack and Mach number at transonic and supersonic speeds
Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and in Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form. Results regarding the center-of-pressure shift due to angle of attack, center-of-pressure shift due to Mach number, and combined effects of angle of attack and Mach number are provided.
An Investigation of Scaling of Zirconium at Elevated Temperatures Quarterly Status Report no. 9.June 2, 1955 to Sept. 2, 1955
To obtain a better understanding of the mechanism involved in scaling behavior of zirconium, kinetic studies were made of the weight pickup in air after the following pretreatments; (1) exposure to oxygen or nitrogen, (2) exposure to air, oxygen or nitrogen and removal of the resulting surface compounds.
The Mechanical Properties of Beta-Quenched Uranium at Elevated Temperatures
The creep strength and tensile properties-were determined in vacuum for beta-quenched, derby uranium. The stresses to produce a secondary creep rate of- 0.0001 per cent per hr at 100, 250, 400, and 500 deg C were 48,000, sile strengths were 114,500, 35,100, 11,100, and 8,500 psi at temperatares of 28, 300, 500, and 700 deg C, respectively. The creep and tensile strengths decrease quite rapidly with increasing temperature in the temperatare range 250 to 400 deg C.
Redox Ventilation Study Recommendation Report
This report describes a proposed modification to the ventilation system in the Redox Canyon Building. Detailed drawings and cost estimates are provided for three alternatives.
Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles
Report presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute minimum cooling-air requirements.
Design and test of mixed-flow impellers 6: performance and parabolic-bladed impeller with shroud redesigned by rapid approximate method
Report presenting a centrifugal impeller with a modified design procedure to reduce the velocity gradients existing along the hub from inlet to outlet. The modified impeller had better performance characteristics than the original at all speeds tested.
The Effects of Reactor Irradiation of Thorium-Uranium Alloy Fuel Plates
Several plates of 98.7% Th - 1.2% U 235 (clad in aluminum) were irradiated in the MTR for an integrated flux of 2.6 x 10 21 neutrons/cm2. Although these samples represent an early development in bonding of aluminum to thorium and there are better methods at present, the bond proved to be quite strong and both clad and core were dimensionally stable under irradiation. The production of uranium 233 was as much as theory would indicate and the total amount of fissionable material material after irradiation and after decay of the protactinium 233 was greater than before irradiation. A fuel element of this nature appears to offer excellent potentialities from the standpoint of radiation stability.
Final Report: Airborne Reconnaissance Project Dripping Spring, Quartzite, Gila County, Arizona
Abstract: A low-level airborne radiometric survey of the younger pre-Cambrian Dripping Spring quartzite, undertaken in the mountainous region lying roughly 100 riles east of Phoenix, was completed June 3, 1955. Twenty-seven radioactive anomalies were located. To date seven of these have produced uranium ore, four more will probably become producers, and six others may possibly become producers. Flying was concentrated in the Dripping Spring quartzite, but reconnaissance flights were made over other formations. Private prospecting, both from the air and on the ground, increased considerably when the airborne project started. Eleven of the private discoveries have produced ore, and many others show considerable promise.
A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 2
Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.
ORNL Metal Recovery Plant Processing Clementine Reactor Fuel Elements: Terminal Report
This report presents data obtained from processing 33 Clementine Reactor fuel elements in the ORNL Metal Recovery Plant to recover approximately 15 kg of plutonium and 0.16 g of americium.
Performance characteristics of axisymmetric two-cone and isentropic nose inlets at Mach number 1.90
Report presenting an experimental investigation at Mach number 1.90 to determine the overall performance capabilities of axisymmetric two-cone and isentropic nose inlets in terms of total-pressure recovery, mass flow, and external drags. At zero angle of attack, the external drag was separated into their components of cowl pressure, friction, and additive drags. Results regarding total-pressure recovery and mass-flow characteristics, total-pressure profiles at diffuser exit, cowl-pressure distributions and drag, zero-angle-of-attack component breakdown of external drag, and overall performance comparison are provided.
Practical Methods for the Reduction of Strain Gage Data
The error that results when it is attempted to evaluate stress from a reading taken on a single element SR-4 strain gage in a biaxial stress field is discussed. A method is presented for relating SR-4 rosette strain gage readings directly to the biaxial stress state without the necessity of first converting strain gage readings to true strains. Correction formulas are presented for use when single element SR-4 gages are used as rosette elements or as stress gages.
Preliminary experimental investigation of a variable-area, variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44
Report presenting a preliminary investigation of a variable-area, variable-internal-contraction air inlet at a range of Mach numbers. The total pressure recovery after supersonic compression, total pressure recovery at the exit of the subsonic diffuser, and the pressure distribution along the diffuser walls were measured.
A variable-geometry axisymmetric supersonic inlet with telescoping centerbody
Report presenting an examination of the use of an axisymmetric variable-geometry technique for achieving good supersonic inlet performance over a wide range of Mach numbers. An inlet with a telescoping spike was designed and experimentally evaluated. Results regarding the spike survey study and variable-geometry-inlet study are provided.
Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades
Report presenting an investigation of the stress distribution in the roots of the first three stages of the J6S axial-flow compressor in order to explain root failures experienced in service. Root failures were producible in the lab when high vibratory stresses were combined with simulated centrifugal loads. Results regarding fatigue tests on the original J6S blade roots and on two redesigned blade roots as well as a comparison of the different root designs are provided.
The Coulometric Titration of Plutonium
This work was performed to develop a general chemical method for the determination of small amounts of plutonium in solution. The work showed that a coulometric titration based on the preliminary oxidation of the plutonium to Pu (VI) followed by titration with electrolytically-generated ferrous ion to Pu (IV) was such a general method and was subject to few interferences. The significance of the work is that a chemical determination of plutonium can be made for amounts of plutonium heretofore determined only by radioassay methods, and the chemical determination of larger amounts are made more readily and with higher precision than with previous methods. The work also extends the application of coulometric titration methods to a new substance.
Interaction of a Jet and Flat Plate Located in an Airstream
Report presenting an evaluation of the interaction between a flat plate and a nearby jet issuing from a convergent nozzle over a range of pressure ratios and free-stream Mach numbers. The effect on the interaction of the presence of streamline, blunt-base, and curved-base fairings between the plate and parabolic afterbody housing the exit nozzle was also investigated.
Investigation of the compressive strength and creep lifetime of 2024-T3 aluminum-alloy plates at elevated temperatures
The results of elevated-temperature compressive strength and creep tests of 2024-t3 (formerly 24s-t3) aluminum alloy plates supported in v-grooves are presented. The strength-test results indicate that a relation previously developed for predicting plate compressive strength for plates of all materials at room temperature is also satisfactory for determining elevated-temperature strength. Creep-lifetime results are presented for plates in the form of master creep-lifetime curves by using a time-temperature parameter that is convenient for summarizing tensile creep-rupture data. A comparison is made between tensile and compressive creep lifetime for the plates and a method that made use of isochronous stress-strain curves for predicting plate-creep failure stresses is investigated.
Performance Characteristics of Several Divergent-Shroud Aircraft Ejectors
Report presenting an investigation of ten divergent- and two cylindrical-shroud ejectors to determine internal ejector performance over a range of pressure ratios and expansion area ratios for Mach numbers up to about 3. Results regarding jet-thrust and air-handling characteristics and net-thrust performance are provided.
Radiochemical Analyses for Fe, Cr, Ni, and Co Corrosion Products
Abstract: Radiochemical and carrier techniques have been applied to the determination of minute amounts of Fe, Cr, Ni, and Co which appear as corrosion products of Inconel. The results are as follows: Fe, 0.061 per cent; Cr, 0.15 per cent; Ni, 0.037 per cent; and Co, .0005 per cent.
Determination of Corrosion Products and Additives in Homogenous Reactor Fuel II. Polarographic Determination of Chromium
A satisfactory ion-exchange-polarographic method was developed for the determination of either chromium(VI) or total chromium in Homogeneous Reactor fuels. Total chromium is determined as chromium (VI) , i.e., chromate, and in the same way as is chromium(VI), after chromium in the lower valence states is oxidized to chromate by potassium permanganate. Chromate is separated from all interfering metal ions in the fuel by ion exchange on a Dowex 50 resin column. The Chromate in the effluent is determined polarographically in approximately 0.75 M sodium hydroxide solution as supporting electrolyte. A well polarographic wave is obtained for the chromium (VI) chromium (III) reduction at a half-wave potential of -0.85 volt vs. the S.C.E. The relative standard deviation of the data for 2 μg of chromium (VI) per ml was 2%; for 4 μg of total chromium per ml, it was 3%. An ion-exchange-polarographic method was developed also for the determination of chromium(III). Chromium (III) is separated from all interfering ions in the fuel by ion exchange on a Dowex 1 resin column. The chromium (III) in the effluent is determined polarographically in a 1M ammonia-1M ammonium chloride supporting electrolyte. The wave obtained at a half-wave potential of -1.42 volt vs. the S.C.E is poorly defined, and the method is not entirely satisfactory.
APOTA (Automatic Positioning of Telemetering Antennas)
This report presents a description of and operating instructions for APOTA--a device which automatically tracks any signal-emitting source within the 190 to 250 MC band. APOTA is especially useful for telemetering applications.
An Evaluation of a Rolleron-Roll-Rate-Stabilization System for a Canard Missile Configuration at Mach Numbers From 0.9 to 2.3
Report presenting a linear stability analysis and flight-test investigation on a rolleron-roll-rate stabilization system for a canard missile. This type of damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by introducing control-surface damping about the rolleron hinge line.
Longitudinal Characteristics at Transonic and Supersonic Speeds of a Rocket-Propelled Airplane Model Having a 60-Degree Delta Wing and Low Swept Horizontal Tail
Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.
A method for simulating the atmospheric entry of long-range ballistic missiles
From Summary: "It is demonstrated with the aid of similitude arguments that a model launched from a hypervelocity gun upstream through a special supersonic nozzle should experience aerodynamic heating and resulting thermal stresses like those encountered by a long-range ballistic missile entering the earth's atmosphere. This demonstration hinges on the requirements that model and missile be geometrically similar and made of the same material, and that they have the same flight speed and Reynolds number (based on conditions just outside the boundary layer) at corresponding points in their trajectories. The hypervelocity gun provides the model with the required initial speed, while the nozzle scales the atmosphere, in terms of density variation, to provide the model with speeds and Reynolds numbers over its entire trajectory."
Note on Hovering Turns with Tandem Helicopters
"The source of an appreciable pitching-moment difference between left and right hovering turns for a tandem helicopter is described. The difference in pitching moment results from the difference in rotational speed of the counter rotating rotors with respect to the air while the helicopter is turning" (p. 1).
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61
Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The report presents data on a configuration which simulated a fighter-bomber airplane with a large and a small external store.
The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations 3: swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61
Report presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.61. Separate forces on a store, a swept wing, and a swept-wing-fuselage combination were measured. This report presents data on a configuration that simulated a fighter-bomber airplane with a large and a small external store.
Transonic Wind-Tunnel Investigation of the Aerodynamic Loading Characteristics of a 60 Degree Delta Wing in the Presence of a Body With and Without Indentation
Report presenting an investigation in the transonic pressure tunnel to determine the aerodynamic loading characteristics of a 60 degree delta wing in the presence of a body with and without body indentation in accordance with the transonic-area-rule concept. Tests covered a range of angles of attack and Mach numbers. Results regarding force and moment coefficients and curves are provided.
Automatic Isotope Mass Spectrometer : Job Specification JS-741, Rev. 2
The following document analyzes the Automatic Isotope Mass Spectrometer that consists of a Laboratory Isotope Mass Spectrometer, covered by Union Carbide Nuclear Company Job Specification "JS-747", which has been modified to meet Union Carbide Nuclear Company Job Specification "JS-741", as well as the instrument's samples collected and analyzed.
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