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Effect of Rate of Temperature Change on the Transformations in an Alloy Steel

Description: Scientific paper issued by the Bureau of Standards over studies conducted on the effects of temperature change on alloy steel. The experimental methods used and the results are presented and discussed. This paper includes tables, photographs, and illustrations.
Date: July 10, 1919
Creator: Scott, Howard
Partner: UNT Libraries Government Documents Department
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Effect of variation of chord and span of ailerons on rolling and yawing moments in level flight

Description: This report presents the results of an investigation of the rolling and yawing moments due to ailerons of various chords and spans on two airfoils having the Clark Y and U. S. A. 27 wing sections. Some attention is devoted to a study of the effect of scale on rolling and yawing moments and to the effect of slightly rounding the wing tips. The results apply to level flight with the wing chord set at an angle of attack of +4 degrees and to conditions of zero pitch, zero yaw, and zero roll of the … more
Date: July 10, 1928
Creator: Heald, R. H. & Strother, D. H.
Partner: UNT Libraries Government Documents Department
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Investigation of the Photochemical Method for Uranium Isotope Separation

Description: To find a process for successful photochemical separation of isotopes several conditions have to be fulfilled. First, the different isotopes have to show some differences in the spectrum. Secondly, and equally important, this difference must be capable of being exploited in a photochemical process. Parts A and B outline the physical and chemical conditions, and the extent to which one might expect to find them fulfilled. Part C deals with the applicability of the process.
Date: July 10, 1943
Creator: Urey, H.C.
Partner: UNT Libraries Government Documents Department
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Healing of Fast-Neutron-Induced Changes in Graphite. II. The Effect of Heating During Exposure, Interim Report on Problem 323 MLC 2301

Description: Technical report. The effect of temperature during pile exposure on the fast-neutron-induced change in properties of graphite was studied. Temperatures up to 125 degrees C have no effect upon the rate of increase of elastic modulus; pieces exposed at 300 degrees C on the other hand show no change at all in elastic modulus. The increase in electrical resistance s an inverse function of the temperature of exposure at all temperatures in the range 60 to 300 degrees C.
Date: July 10, 1944
Creator: Neubert, Thomas A.; Novick, A.; Schenck, R. & Shapiro, E.
Partner: UNT Libraries Government Documents Department
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Studies of the hemolytic effect of radiation

Description: These studies were aimed at elucidating affects of radiation in inducing hemolysis independent of inhibition of erythropoiesis. Research studies were conducted both on human patients and dogs. Phosphorus-32 in mc amounts were administered either intravenously or orally to patients suffering Polycythemia rubra vera. Dogs were treated with either P-32 or x-radiation. Hemoglobin metabolism was monitored in all test subjects by hematology, blood chemistry, and fecal excretion of hemoglobin cataboli… more
Date: July 10, 1945
Creator: Schwartz, S.; Katz, E.; Porter, L.M.; Jacobson, L.O. & Watson, C.J.
Partner: UNT Libraries Government Documents Department
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Investigation of the Loads on a Typical Bubble-Type Canopy

Description: Report presenting an investigation of the surface pressures of the outer and inner surface of the bubble-type canopy in order to determine their load requirements. Testing was performed on a Grumman F8F-1 airplane. The forces on the canopy was found to be the highest when the airplane is operating at high speed with the canopy closed.
Date: July 10, 1947
Creator: Cocke, Bennie W., Jr.
Partner: UNT Libraries Government Documents Department
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Tuft Studies of the Flow over a Wing at Four Angles of Sweep

Description: Studies of the stalling characteristics show that the stall begins at the tip and moves inboard with increasing angle of attack at positive sweep; the sta11 begins at root and moves outboard at negative sweep (sweepforward). At +/-45 deg sweep the stall was less sharply defined than at the lower angles of sweep. No effect of Mach number on the.flow patterns as indicated by tufts was found in the speed range of these tests which extended to a Mach number of 0.55.
Date: July 10, 1947
Creator: Hieser, Gerald
Partner: UNT Libraries Government Documents Department
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Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle

Description: An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowe… more
Date: July 10, 1950
Creator: Grey, Ralph E.; Brightwell, Virginia L. & Barson, Zelmar
Partner: UNT Libraries Government Documents Department
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Effect of Mach Number on Over-All Performance of Single-Stage Axial-Flow Compressor Designed for High Pressure Ratio

Description: "A complete stage of an axial-flow compressor designed to produce a high pressure ratio was investigated at speeds from 110 to 130 percent of design speed (836 ft/sec). The data obtained and the results of a previous investigation of the same compressor at speeds from 50 to 100 percent of design speed were used to determine the effect of Mach number on over-all performance. The peak total-pressure ratio increased from 1.095 to 1.515 and the peak adiabatic efficiency decreased from 0.93 to 0.89 … more
Date: July 10, 1950
Creator: Voit, Charles H.; Guentert, Donald C. & Dugan, James F.
Partner: UNT Libraries Government Documents Department
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Performance of 24-inch supersonic axial-flow compressor in air 3: compressor performance with inlet guide vanes

Description: The use of inlet guide vanes with the 24-inch supersonic compressor resulted in a decrease in maximum pressure ratio and adiabatic efficiency, and a slight increase in equivalent mass flow. The loss in total pressure and efficiency resulted from reduced diffusion in the rotor-blade passages, increased shock losses at the higher entrance Mach number, and increased mixing separation, and transfer of mass flow toward the rotor hub. The unsteady flow field created at the compressor entrance by the … more
Date: July 10, 1950
Creator: Hartmann, Melvin J. & Tysl, Edward R.
Partner: UNT Libraries Government Documents Department
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Compilation and review of effects of design parameters on ditching characteristics

Description: From Summary: "This paper supplements a previously published one on the effect of design parameters on ditching characteristics. The supplementary information is based on additional data available from both model tests and full-scale experience. In addition, summary tables compiled from the NACA model ditching investigations are presented."
Date: July 10, 1951
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department
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Effects of spanwise thickness variation on the aerodynamic characteristics of 35 degree and 45 degree sweptback wings of aspect ratio 6: transonic-bump method

Description: Report presenting an aerodynamic investigation in the high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamic characteristics of wings with 35 and 45 degrees of sweepback, aspect ratio 6, and taper ratio 0.60. The wings were tested over a range of Mach numbers.
Date: July 10, 1951
Creator: Morrison, William D., Jr. & Fournier, Paul G.
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of the Longitudinal Stability and Control of a Rocket-Propelled Missile Model Having Cruciform, Triangular, Interdigitated Wings and Tails

Description: Report presenting flight testing of a missile model with cruciform, triangular, interdigitated wings and tails to determine the longitudinal stability and control characteristics over a range of Mach numbers. Results regarding static stability and damping, control effectiveness, and control hinge moments are provided.
Date: July 10, 1951
Creator: Sandahl, Carl A. & Hall, James R.
Partner: UNT Libraries Government Documents Department
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Graphite Sample Boring from Process Channels : Final Report, Production Test 105-389-P

Description: The following report records a total of forty-nine graphite core samples that have been bored from process tube blocks in the Hanford piles with the intention to provide results to indicate that core boring is an entirely practical operation over bore scraping in obtaining powder samples.
Date: July 10, 1951
Creator: Cole, J. B.
Partner: UNT Libraries Government Documents Department
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Graphite Sample Boring from Process Channels : Final Report, Production Test 105-389-P

Description: The following report records a total of forty-nine graphite core samples that have been bored from process tube blocks in the Hanford piles with the intention to provide results to indicate that core boring is an entirely practical operation over bore scraping in obtaining powder samples.
Date: July 10, 1951
Creator: Cole, J. B.
Partner: UNT Libraries Government Documents Department
open access

Low-Speed Investigation of Several Types of Split Flap on a 47.7 Degree Sweptback-Wing - Fuselage Combination of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Description: Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a 47.7 degree sweptback wing-fuselage combination with split flaps and several modifications. The lift characteristics, pitching-moment characteristics, drag characteristics, and a comparison with flaps of the slotted type are included.
Date: July 10, 1951
Creator: Spooner, Stanley H. & Mollenberg, Ernst F.
Partner: UNT Libraries Government Documents Department
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Pile modification resulting in increased power levels

Description: The power output of the piles is being restricted primarily by three important limitations; those due to graphite temperatures, slug and tube corrosion and maximum power per tube or ``boiling disease.`` The purpose of this document is to present means for increasing very appreciably the ``boiling disease`` limits. In addition, means for alleviating the corrosion limitations will be discussed.
Date: July 10, 1951
Creator: Carbon, M. W. & Fryar, R. M.
Partner: UNT Libraries Government Documents Department
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Production Test 105-389-P graphite sample boring from process channels. Final report

Description: The study of radiation damage to the graphite moderator is largely dependent upon the availability of graphite samples from the moderator itself. Because of the varied temperature-flux history and complicated structure of the piles, it is impossible to study the problem from the laboratory standpoint alone. The samples of greatest interest are those taken from the sections of the moderator which have received the greatest damage. However, a comprehensive study requires samples from all sections… more
Date: July 10, 1951
Creator: Cole, J. B.
Partner: UNT Libraries Government Documents Department
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A Solvent Extraction Method for Neptunium (237) Analysis

Description: Technical report describing a rapid and quantitative radiochemical method for the analysis of neptunium (237). This method is based on the extraction of neptunium (IV) with thenoyl-trifluoracetone in xylene. Neptunium (237) is separated free from other alpha emitters and from non-radioactive interferences, and the method may be readily adapted to remote control. [From Abstract]
Date: July 10, 1951
Creator: Moore, Fletcher L.
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of an Automatic Control System With Primary Sensitivity to Normal Accelerations as Used to Control a Supersonic Canard Missile Configuration

Description: Report presenting a theoretical investigation of an automatic control system with primary sensitivity to normal accelerations as used to control a specific supersonic canard missile. The control system is made up of an integrating servomotor that receives a signal from an accelerometer that is sensitive to normal accelerations of the airframe that it is controlling. The acceleration control system appears to work well for obtaining longitudinal control, but works best when combined with a homin… more
Date: July 10, 1951
Creator: Seaberg, Ernest C. & Smith, Earl F.
Partner: UNT Libraries Government Documents Department
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Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers

Description: Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date: July 10, 1952
Creator: Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
Partner: UNT Libraries Government Documents Department
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Effect of trailing edge thickness on lift at supersonic velocities

Description: Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date: July 10, 1952
Creator: Chapman, Dean R. & Kester, Robert H.
Partner: UNT Libraries Government Documents Department
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