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Temperature Measurements in Bessemer and Open-Hearth Practice

Description: Technical paper issued by the Bureau of Standards over studies conducted on different types of furnaces, specifically the Bessemer and the open-hearth furnace. The results of the studies are presented and discussed. This paper includes tables, and illustrations.
Date: May 8, 1917
Creator: Burgess, George K.
Partner: UNT Libraries Government Documents Department
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Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail … more
Date: May 8, 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department
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Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers

Description: "Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail… more
Date: May 8, 1944
Creator: Flight Research Maneuvers Section
Partner: UNT Libraries Government Documents Department
open access

Tests of Air Valves for Intermittent-Jet Engines at Speeds of 20 and 25 Cycles Per Second

Description: Report discussing a study of automatic nonreturn air valves for use in an intermittent-jet engine. Four valve-spring materials, three valve-grill materials, and five types of valves were used. Valve A, which was made out of aluminum, was found to perform the best and last the longest.
Date: May 8, 1945
Creator: Bressman, Joseph R. & McCready, Robert J.
Partner: UNT Libraries Government Documents Department
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Production test 105-2-P (Supplement A) - Activity of pile discharge water (Activation of manganese and iron)

Description: This report discusses the Production Test 105-2-P (Supplement A) -- Activity of Pile Discharge Water. Previous studies of pile discharge water have shown that one of two processes is responsible for the large but variable amount of Mn{sup 56} activity present in the water. One process is the production of Mn{sup 56} by the reaction Mn{sup 55} on manganese impurity in the water. The amount of such impurity has been shown to be too small to produce the observed amount of Mn{sup 56} unless the mea… more
Date: May 8, 1946
Creator: West, J.M.
Partner: UNT Libraries Government Documents Department
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The Toxicity and Metabolism of Plutonium in Laboratory Animals

Description: Introduction. The main objective of the Metallurgical Project was the preparation of large quantities of plutonium 239, an isotope of element 94, by the interaction of neutrons and uranium. At the beginning, only predictions of its chemical and biological properties could be made since it is a new element. It was predicted that it would be toxic to tissue by virtue of its high atomic weight, and in addition, that it would be toxic by virtue of its radioactivity. Thus, the preparation and use… more
Date: May 8, 1947
Creator: Finkle, Raymond D.; Snyder, Robert H.; Jacobson, Leon O.; Kisieleski, Walter E.; Lawrence, Blanche. & Simmons, Eric L.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of the wing alone and of the wing-fuselage configurations employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A004 airfoil section parallel to the air stream. The experimental results of a wing of identical plan from having an NACA 65A006 airfoil section which was tested as part of the transonic program are presented in reference 1.
Date: May 8, 1950
Creator: Myers, Boyd C., II & Wiggins, James W.
Partner: UNT Libraries Government Documents Department
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Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds

Description: Report presenting an investigation concerned with the measurement of the characteristics of longitudinal-control devices for a wing-fuselage combination with a wing with the leading edge swept back 63 degrees. Most of the investigation was devoted to testing a 30-percent-chord, 50-percent-semispan elevon, but some used upper-surface spoilers. Results regarding the characteristics of the wing with the elevon undeflected and control-surface effectiveness are provided.
Date: May 8, 1950
Creator: Olson, Robert N. & Mead, Merrill H.
Partner: UNT Libraries Government Documents Department
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Characteristics of perforated diffusers at free-stream Mach number 1.90

Description: "An investigation was conducted at Mach number 1.90 to determine pressure recovery and mass-flow characteristics of series of perforated convergent-divergent supersonic diffusers. Pressure recoveries as high as 96 percent were obtained, but at reduced mass flows through the diffuser. Theoretical considerations of effect of perforation distribution on shock stability in converging section of diffuser are presented and correlated with experimental data. A method of estimating relative importance … more
Date: May 8, 1950
Creator: Hunczak, Henry R. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department
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An empirically derived basis for calculating the area, rate, and distribution of water-drop impingement on airfoils

Description: From Summary: "An empirically derived basis for predicting the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The concepts involved represent an initial step toward the development of a calculation technique which is generally applicable to the design of thermal ice-prevention equipment for airplane wing and tail surfaces. It is shown that sufficiently accurate estimates, for the purpose of heated-wing design, can be obtained by a few numer… more
Date: May 8, 1951
Creator: Bergrun, Norman R.
Partner: UNT Libraries Government Documents Department
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Sound from a two-blade propeller at supersonic tip speeds

Description: Report presenting sound measurements at static conditions for a two-blade, 47-inch-diameter propeller over a range of tip Mach numbers. For comparison, spectrums have been obtained at both subsonic and supersonic tip speeds. Results regarding the experimental results and comparison with theory are provided.
Date: May 8, 1951
Creator: Hubbard, Harvey H. & Lassiter, Leslie W.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) 2: aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

Description: Report presenting an experimental investigation to determine the aerodynamic load distributions of a series of five bodies with conical or slightly blunted noses and cylindrical afterbodies in the 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at Mach number 3.12 for a range of Reynolds numbers and angles of attack.
Date: May 8, 1952
Creator: Jack, John R. & Gould, Lawrence I.
Partner: UNT Libraries Government Documents Department
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An experimental cascade study of the effects of a solidity reduction on the two-dimensional aerodynamic characteristics of a turbine-rotor blade suitable for air cooling

Description: Report presenting an experimental two-dimensional investigation of the mechanism of the flow and losses involved in the operation of a low-solidity highly loaded turbine-blade profile suitable for use in an air-cooled turbine, which has been made in a cascade.
Date: May 8, 1952
Creator: Plohr, Henry W. & Nusbaum, William J.
Partner: UNT Libraries Government Documents Department
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Sites of Azaserine Inhibition During Photosynthesis byScenedesmus

Description: The success attending the use of azaserine as a specific inhibitor of one atage in the metabolic pathway leading to the synthesis of inosinic acid in pigeon liver prompted us to use this antibiotic in a similar attack on purine synthesis in Scenedesmus. However, investigation of the products produced during photosynthesis by suspensions of these algae in the presence of azaserine showed that a more widespread interference with metabolism had occurred. The purpose of this communication is to des… more
Date: May 8, 1956
Creator: Barker, S. Alan; Bassham, James A.; Calvin, M. & Quarck, Ursula C.
Partner: UNT Libraries Government Documents Department
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Progress Report on Scintillation and Other Related Properties of Unactivated NaI Crystals

Description: This is a progress report on the investigation of "Scintillation and Other Related Properties of Unactivated NaI Crystals" for the period January 1, 1957 to March 31, 1957. The principal results of the experimental efforts during this time have been the determination of conversion efficiency and some more detailed examinations of decay time.
Date: May 8, 1957
Creator: Van Sciver, W. J.
Partner: UNT Libraries Government Documents Department
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A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Memorandum presenting lift and drag characteristics that have been determined in flight in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements, including various wing boundary-layer-control installations. Minimum comfortable approach speeds for carrier-type landings were evaluated for these airplanes by four test pilots. Results regarding the presentation of data, methods for the prediction of minimum comfortable approach speed, reasons for limiting approac… more
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Partner: UNT Libraries Government Documents Department
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A Comparison of Flight-Measured Carrier-Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations

Description: Report presenting lift and drag characteristics in the landing-approach configuration on 41 jet-propelled fighter-type airplane arrangements using flight testing. Minimum comfortable approach speeds were evaluated by four test pilots. Suggestions for achieving optimal speeds for approach under various conditions are also provided.
Date: May 8, 1958
Creator: White, Maurice D.; Schlaff, Bernard A. & Drinkwater, Fred J., III
Partner: UNT Libraries Government Documents Department
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Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone

Description: Report presenting testing of two blunt-nose models, a flat-face-cone and a hemisphere-cone, at Mach numbers up to 4.7. The main purpose was to determine information about heating rates and transition for different blunt nose shapes for long-range ballistic missiles. Information about pressure measurements and heat transfer is provided.
Date: May 8, 1958
Creator: Speegle, Katherine C.; Chauvin, Leo T. & Heberlig, Jack C.
Partner: UNT Libraries Government Documents Department
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Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: Memorandum presenting results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane. Tests at Mach number 6.86 were made on the scaled model and on several other configurations with lower stiffnesses.
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Partner: UNT Libraries Government Documents Department
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Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter

Description: "Results of tests for possible flutter of a dynamically and elastically scaled model of a proposed all-movable horizontal tail surface for the North American X-15 airplane are presented herein. Tests at a Mach number of 6.86 were made on the scaled model and on several other configurations having lower stiffness. Flexibility influence coefficients and calculated modes and frequencies for the weakest configuration are presented" (p. 1).
Date: May 8, 1958
Creator: Lauten, William T., Jr.; Levey, Gilbert M. & Armstrong, William O.
Partner: UNT Libraries Government Documents Department
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Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components

Description: Memorandum presenting an investigation to determine the performance of the XJ79-GE-1 turbojet engine and its components, while operating as integral parts of the engine, conducted in an altitude test chamber. Data were obtained over a range of Reynolds number indices and for various settings of the variable compressor stators and variable-area exhaust nozzle from fully open to fully closed positions. Results regarding the component performance and engine performance are provided.
Date: May 8, 1958
Creator: Campbell, Carl E.
Partner: UNT Libraries Government Documents Department
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Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs

Description: Report presenting testing of four multiweb wing models were tested at Mach number 2 in a free jet to investigate structural effects of aerodynamic heating and loading. All of the models were the same except for the number of chordwise internal stiffening ribs; each had zero, one, two, or three. Results regarding laboratory vibration tests, jet tests, model behavior, temperatures, stresses, and discussion of failure are provided.
Date: May 8, 1958
Creator: Davidson, John R.; Rosecrans, Richard & Vosteen, Louis F.
Partner: UNT Libraries Government Documents Department
open access

Critical Incident Alarm - Model I Instruction and Maintenance Manual

Description: The HAPO Critical Incident Alarm, Model I, is an instrument designed to give an audible and visual alarm signal in the event of a critical incident to which it is exposed. There will be thirty-one (31) of these instruments installed and several spares located in the various manufacturing buildings in the Chemical Processing Department where there exists any possibility of a critical incident occurring. The instrument is intended as a post or after-the-fact warning device. It will offer no prote… more
Date: May 8, 1959
Creator: Kelly, P. R.
Partner: UNT Libraries Government Documents Department
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