Technical Report Archive & Image Library (TRAIL) - 66 Matching Results

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Neutron Emission by Polonium Oxide Layers

Description: The following report calculates how many neutrons are produced by the O-16([alpha]-n) reaction in a thin and uniform polonium oxide layer.
Date: August 8, 1944
Creator: Argo, M. & Teller, E.
Partner: UNT Libraries Government Documents Department
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Consolidation and shaping of boron ; summary of previous work

Description: From abstract: "The deposit on the rods is in the form of a brittle uneven tube which is cracked off and subsequently pulverized to a 200-mesh powder. This report is chiefly concerned with methods of consolidating this powder and shaping it into forms required, though it also discusses to some extent other methods of shaping boron or born-rich materials."
Date: October 8, 1945
Creator: Kamm, Robert L.
Partner: UNT Libraries Government Documents Department
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Methyl Methacrylate Casting Resin

Description: Abstract: "This report describes work done to improve the casting characteristics of methyl methacrylete resin under CMR-6-18 authorization. The experimental program was initiated with the objectives of decreasing casting time, bubble formation and shrinkage. It has been found that by use of a common solvent for monomer and polymer concentration in monomer can be attained greater than any previously reported in preparation of a methacrylate casting resign. Incorporation of this greater amount o… more
Date: January 8, 1948
Creator: Church, J. S. & Tyler, H. R.
Partner: UNT Libraries Government Documents Department
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The Effect of Age on the Radiosensitivity of Mice

Description: Abstract: Mice of different ages ranging from 1.5 to 12 months have been exposed to gamma rays in an effort to determine the change in radiosensitivity with age. The dose necessary to cause 50% killing was determined for each age group and sex. No change in sensitivity with age was observed with either sex, although the experimental error in the case of the males was quite large. The females were found to be more resistant than the males.
Date: April 8, 1946
Creator: Curtis, H. J.; Zirkle, Raymond E. (Raymond Elliot), 1902-1988; Anderson, Ernest C., 1920-2013 & Riley, E. F.
Partner: UNT Libraries Government Documents Department
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Slug Jacket Temperatures

Description: Abstract. A method for calculating jacket temperatures in a region of varying heat transfer coefficients is given Some applications are made for temperatures above a supporting rib.
Date: November 8, 1944
Creator: Schlegel, Richard, 1913-
Partner: UNT Libraries Government Documents Department
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The Solubility of Uranyl Oxalate and the Existence of Undissociated Uranyl Oxalate in Solution

Description: Abstract: "The solubility of the solid, UO2C2O4 x rH2O, was measured at various acid and uranyl nitrate concentrations. The results of the measurements prove the existence of the uranyl oxalate complex - UO2C2O4, in solutions containing excess UO2^2."
Date: September 8, 1945
Creator: Pimentel, George C. & Stevenson, F. R.
Partner: UNT Libraries Government Documents Department
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The Metal-Dielectric Junction of High-Voltage Insulators in Vacuum and Magnetic Field

Description: From introduction: "This study is concerned with the shape of the electrodes of high-voltage insulator and with the method of joining them to the dielectric. The study is limited to insulators operating in vacuum, with special interest in the cases where strong magnetic fields are present. It is further limited to insulators with the high-voltage electrodes maintained at negative potential. The object of the study was to obtain information that would aid in improving the design of the insulator… more
Date: August 8, 1945
Creator: Kjofoid, M. J.; Alger, Raymond S. & Graves, D.
Partner: UNT Libraries Government Documents Department
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Comparative Drag Measurements at Transonic Speeds of 6-Percent-Thick Airfoils of Symmetrical Double-Wedge and Circular-Arc Sections From Tests by the NACA Wing-Flow Method

Description: Report presenting comparative drag measurements at zero lift at transonic speeds for two sharp-leading-edge airfoils using the NACA wing-flow method. One airfoil had a symmetrical circular-arc section and one had a symmetrical double-wedge section. The primary difference in the drag characteristics of the two airfoils at zero lift is the earlier drag rise of the double-wedge section.
Date: April 8, 1947
Creator: Silsby, Norman S.
Partner: UNT Libraries Government Documents Department
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Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing

Description: Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date: December 8, 1947
Creator: Mathews, Charles W. & Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
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Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet

Description: Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date: June 8, 1948
Creator: Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
Partner: UNT Libraries Government Documents Department
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Notes on Geared Tabs at Supersonic Speeds

Description: Memorandum presenting an analysis of the two-dimensional, geared, trailing-edge flap-tab combination at supersonic speeds to determine if the combination could be used to reduce the hinge moments to extremely small values while retaining a large part of the lift effectiveness of a plain flap with the same ratio of flap chord to wing chord.
Date: July 8, 1948
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a Swept-Back Wing Having Inverse Taper as Determined by Flight Tests at Supersonic Speeds

Description: Report discussing the results of flight tests to determine the drag at zero lift of a swept-back wing of inverse taper using an NACA 65-009 airfoil. The data was compared to untapered wings with a similar degree of sweepback. The tapered wing was found to have a lower drag coefficient than the 34-degree swept-back untapered wing but a higher drag coefficient than the 45-degree swept-back untapered wing.
Date: April 8, 1947
Creator: Alexander, Sidney R.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of thrust augmentation of axial-flow-type 4000-pound-thrust turbojet engine by water and alcohol injection at compressor inlet

Description: Report presenting an experimental investigation of thrust augmentation of an axial-flow-type turbojet engine with a 4000-pound-thrust rating using a water-alcohol injection at the compressor inlet at sea-level conditions and zero ram. Three injection systems were investigated in order to obtain satisfactory atomization and distribution of the injected liquids. Results regarding engine performance and engine operation are provided.
Date: July 8, 1948
Creator: Baron, Burnett; Dowman, Harry W. & Dackis, William C.
Partner: UNT Libraries Government Documents Department
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Estimated transonic flying qualities of a tailless airplane based on a model investigation

Description: Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date: June 8, 1949
Creator: Donlan, Charles J. & Kuhn, Richard E.
Partner: UNT Libraries Government Documents Department
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High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane: Longitudinal Stability and Control of the D-558-1

Description: Report presenting the results of pitching-moment and lift measurements on a model of the D-558-1 airplane with no nose-inlet flow at several tail and elevator settings at a range of Mach numbers. Information about the stability, control, and downwash results is provided.
Date: July 8, 1948
Creator: Wright, John B.
Partner: UNT Libraries Government Documents Department
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Ice protection of turbojet engines by inertia separation of water 2: single-offset-duct system

Description: Investigation of a single-offset-duct system designed to prevent entrance of water into a turbojet engine was conducted on a half-scale nacelle model. An investigation was made to determine ram-pressure recovery and radial velocity profiles at the compressor section and icing characteristics of such a duct system. At a design inlet velocity of 0.77, the maximum ram-pressure recovery attained with effective water-separating inlet was 77 percent, which is considerably less than attainable with a … more
Date: June 8, 1948
Creator: von Glahn, Uwe
Partner: UNT Libraries Government Documents Department
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Model ditching investigation of the Douglas DC-4 and DC-6 airplanes

Description: Report presenting the ditching characteristics of the Douglas DC-4 and DC-6 in a water tank. Dynamically similar models of 1/16 scale were used for the investigation, which was conducted in calm and rough water. The ditching characteristics and safest ditching procedures were determined by testing at various landing attitudes, speeds, and simulated conditions of damage.
Date: November 8, 1949
Creator: Fisher, Lloyd J. & Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department
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Estimation of Range of Stability Derivatives for Current and Future Pilotless Aircraft

Description: Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.
Date: October 8, 1947
Creator: Pitkin, Marvin & Ankenbruck, Herman O.
Partner: UNT Libraries Government Documents Department
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Tests of the NACA 64-010 and 64A010 Airfoil Sections at High Subsonic Mach Numbers

Description: Memorandum presenting aerodynamic characteristics of the NACA 64-010 and 64A010 airfoil sections as determined from wind-tunnel tests at Mach numbers from 0.3 to 0.9. Comparisons are made which indicate the only significant differences in the characteristics of the two sections to be a consistently greater lift-curve slope and an approximately 10-percent greater maximum section lift coefficient at Mach numbers above 0.7 for the NACA 64-010 airfoil section.
Date: July 8, 1949
Creator: Hemenover, Albert D.
Partner: UNT Libraries Government Documents Department
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Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane

Description: Memorandum presenting wind-tunnel tests of a semispan model of a hypothetical supersonic airplane to determine the static longitudinal stability and control characteristics of the airplane throughout the range of subsonic Mach numbers up to 0.95. The model had a long slender fuselage and a wing and horizontal tail of aspect ratio 4 and taper ratio 0.5. Results regarding the force and moment characteristics, wing wake and effective downwash at the horizontal tail, effects of compressibility, and… more
Date: December 8, 1949
Creator: Johnson, Ben H., Jr. & Rollins, Francis W.
Partner: UNT Libraries Government Documents Department
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An empirical criterion for fin stabilizing jettisonable nose sections of airplanes

Description: "Investigations in the Langley 20-foot free-spinning tunnel of models of five jettisonable nose sections have shown that the airplane nose sections are inherently unstable but can be stabilized by the addition of suitable fins. An empirical criterion has been developed which indicates the fin area required for stabilizing an airplane jettisonable nose section" (p. 1).
Date: December 8, 1949
Creator: Scher, Stanley H.
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics of a Semispan Model of a Supersonic Airplane Configuration at Transonic Speeds From Tests by the NACA Wing-Flow Method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane model with a long slender fuselage, straight wing, and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections. Measurements of the normal force and pitching moments at various angles of attack with five different stabilizer angles of incidence were recorded. The tests were carried out a range of … more
Date: November 8, 1948
Creator: Silsby, Norman S. & McKay, James M.
Partner: UNT Libraries Government Documents Department
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Altitude performance of AN-F-58 fuels in J33-A-21 single combustor

Description: Report discussing three fuels conforming to AN-F-58 specification were investigated in order to determine the influence of boiling temperatures and aromatic content on altitude performance in single combustor of a 4600-pound-thrust turbojet engine.
Date: April 8, 1949
Creator: Dittrich, Ralph T. & Jackson, Joseph L.
Partner: UNT Libraries Government Documents Department
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Some preliminary results in the determination of aerodynamic derivatives of control surfaces in the transonic speed range by means of a flush-type electrical pressure cell

Description: Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.
Date: October 8, 1948
Creator: Erickson, Albert L. & Robinson, Robert C.
Partner: UNT Libraries Government Documents Department
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