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Corrosion Tests : SAE 1010 Mild Steel in Synthetic Neutralized Redox Waste Solution

Description: From introduction: "This report gives the results of a 1000-hour corrosion test of SAE 1010, low carbon steel, in synthetic Redox waste solutions...The present test was designed to obtain corrosion rates for waste solution temperatures of 180 F, 200 F, and 220 F in solutions neutralized to pH values of 11, 12, and 13.
Date: November 13, 1952
Creator: Endow, Noborn
Partner: UNT Libraries Government Documents Department
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Corrosion Test of Type 502 Stainless Steel

Description: The following report provides complete data and test procedure from hot water corrosion tests of type 502 stainless steel.
Date: August 13, 1952
Creator: Zimmerman, D. L.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Sulfamic Acid Tank Valve Failures

Description: This report examines the failure of two 18-8 grade stainless steel gate valves used in sulfamic acid and determines the cause of the failures through a series of tests.
Date: November 13, 1952
Creator: Endow, N.
Partner: UNT Libraries Government Documents Department
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Slug jacket failures, January 1952

Description: There were twenty slug jacket failures during the month of January 1952. Of these, fourteen were end cap failures, five were split slugs and one has not been removed. A total of 311.4 hours of outage time was required for removal of these ruptured slugs from the reactors. The detection, removal and radiation aspects, along with the slug data, are shown on the attached sheets.
Date: February 13, 1952
Creator: Lewis, C. G.
Partner: UNT Libraries Government Documents Department
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Uranium-Copper Deposits Near Copper Canyon Navajo Indian Reservation, Arizona

Description: From introduction: During the summer of 1951, Navajos conducted John W. Chester, Russell C. Cutter, and E. V. Reinhardt, Grand Junction Exploration Branch, U. S. Atomic Energy Commission, to a copper deposit in Copper Canyon. Little radioactivity was noted, and no further work was done in the area at that time. In October 1951, the same group of Navajos reported the discovery of uranium ore in another portion of the same area. The site was visited by Cutter who noted that an excavation made by … more
Date: March 13, 1952
Creator: Reinhardt, E. V.
Partner: UNT Libraries Government Documents Department
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Improvement program -- 234-5 RMA Line

Description: After almost four months elapsed time since product introduction into the RMA Line, it was pertinent to evaluate both process and equipment performance and arrive at a program for future improvement. The suggestions and recommendations provided are those of the Technical Section. In those passages made to acknowledge the views of the appropriate groups.
Date: August 13, 1952
Partner: UNT Libraries Government Documents Department
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Effect of Design Changes of Operating Conditions on Combustion and Operational Performance of a 28-Inch Diameter Ram-Jet Engine

Description: Report presenting an investigation of the altitude performance of a 28-inch diameter ram-jet engine using a direct-connect system in an altitude test chamber. The majority of the investigation occurred at Mach number 2 at altitudes above the tropopause (250 degrees Fahrenheit inlet temperature). Various design configurations were explored and runs were made with different types of fuel.
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department
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A Wind-Tunnel Investigation of the Stability of the Antisubmarine Rocket Mk 1 Mod 0

Description: Report discussing an investigation to determine the cause and provide a fix for the instability in flight of the antisubmarine rocket Mk 1 Mod 0. The Magnus effects and their nonlinear variation with angle of attack were found to affect the stability, so reducing the Magnus effects should reduce instability in the missiles. The greatest reduction of Magnus effects was found through a combination of nose-ring spoiler and the original direction of the propeller rotation, but the nose ring increas… more
Date: November 13, 1952
Creator: Lichtenstein, Jacob H. & Williams, James L.
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. It is shown that, with the antenna stabilized in space, the effect of component lags on the response is small, so that the speed of response is small, so that the speed of response can be made to approach closely that of the airframe alone.
Date: August 13, 1952
Creator: Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of flow fluctuations during surge and blade row stall in axial-flow compressors

Description: "A preliminary investigation of the flow fluctuations of surge and blade row stall was conducted with three single-stage axial-flow compressors with hub-tip ratios of 0.9,0.8, and 0.5 and with a multistage axial-flow compressor. Flow fluctuations of large amplitude associated with stall were detected in all compressors investigated. The fluctuations were caused by low flow regions affecting 25 to 40 percent of the annulus area and propagating in the direction of compressor rotation, but at a lo… more
Date: August 13, 1952
Creator: Huppert, Merle C.
Partner: UNT Libraries Government Documents Department
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Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41

Description: Report presenting an investigation of a series of rectangular wing and body combinations at Mach numbers 1.62, 1.93, and 2.41 to determine the effects of aspect ratio, incidence angle, and forebody length on the interference lift, drag, and pitching moment. A limited investigation to determine the effect of Reynolds number on the wings in the presence of the body was also carried out. Information regarding wing lift, basic quantities for interference evaluation, interference qualities, contribu… more
Date: August 13, 1952
Creator: Coletti, Donald E.
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response

Description: Memorandum presenting a linear theoretical analysis made of the performance of three proportional navigation guidance systems installed in a given supersonic, variable-incidence, boost-glide, antiaircraft missile at Mach numbers of 2.7 and 1.3. Three guidance systems are compared on the basis of the maximum obtainable speed of response of the missile and guidance-system combination consistent with adequate stability. Results regarding the effect of method of positioning the radar antenna on the… more
Date: August 13, 1952
Creator: Abramovitz, Marvin
Partner: UNT Libraries Government Documents Department
open access

Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Description: Report presenting an experimental investigation to determine the thrust augmentation possible by the injection of liquid ammonia into the compressor inlet of an axial-flow-type turbojet engine. Results regarding the selection of coolant, cooling with liquid ammonia, engine performance, and operating experience are provided.
Date: August 13, 1952
Creator: Harp, James L., Jr.; Useller, James W. & Auble, Carmon M.
Partner: UNT Libraries Government Documents Department
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Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor

Description: Report presenting an investigation to determine the importance of molecular-scale processes in the overall turbojet combustion process. The effect of oxygen concentration on the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 combustor was determined for a range of combustor-inlet pressures and a range of fuel-flow rates. At a given fuel-flow rate, combustion efficiency decreased at an increasing rate with reduction in oxygen concentration.
Date: August 13, 1952
Creator: Graves, Charles C.
Partner: UNT Libraries Government Documents Department
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Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: The results of an altitude test-chamber investigation of the effects of a number of design changes and operating conditions on altitude peformance of a 28-inch diameter ram jet engine are presented. Most of the investigation was for a simulated flight Mach number of 2.0 above the tropopause. Fuel-air distribution, gutter width, the presence of a pilot flame, cimbustion-chamber-inlet temperature, and exhaust-nozzle throat area were found to have significant effects on limits of combustion. Combu… more
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department
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Effect of Magnitude of Vibratory Load Superimposed on Mean Tensile Load on Mechanism of and Time to Fracture of Specimens and Correlation to Engine Blade

Description: Memorandum presenting tensile fatigue tests run on seven turbine-blade alloys at a temperature of 1500 degrees Fahrenheit and a mean stress of 22,000 pounds per square inch with superimposed alternating stresses of 0, 5000, 10,000, and 15,000 pounds per square inch. The same three types of fracture occurring in turbine blades - stress-rupture, stress-rupture followed by fatigue, and fatigue - were obtained in the specimens. Results regarding the effect of alternating stress on mechanism of fail… more
Date: November 13, 1952
Creator: Ferguson, Robert R.
Partner: UNT Libraries Government Documents Department
open access

Effect of radiant energy on vaporization and combustion of liquid fuels

Description: Report presenting an investigation of the radiative processes involved in combustion to determine the present role of radiant energy transfer in combustors. The equivalent gray-body emissivity of a hydrocarbon fuel may be increased by use of liquid or solid, soluble or nonsoluble, additives. Results regarding the experimental apparatus and methods, emission characteristics of luminous and nonluminous flames, absorptivity of fuels and of solutions of possible additives, and absorption by slurrie… more
Date: November 13, 1952
Creator: Berlad, A. L. & Hibbard, R. R.
Partner: UNT Libraries Government Documents Department
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Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85

Description: Report presenting an experimental investigation conducted a Mach number of 3.85 to determine the diffuser characteristics of a series of conventional axially symmetric nose inlets on a ramjet in a supersonic wind tunnel. Performance evaluations of single-cone, double-cone, and isentropic diffusers were made in terms of total pressure recovery and mass flow for a range of angles of attack. Results regarding performance of 1-cone inlets, performance of 2-cone inlets, and performance of isentropic… more
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department
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Some observations of flow at the throat of a two-dimensional diffuser at a Mach number of 3.85

Description: Report presenting an experimental investigation at a Mach number of 3.85 in the supersonic wind tunnel to study the flow patterns at the throat of a two-dimensional single-shock diffuser and to evaluate qualitatively several schemes for improving the turning conditions. Schileren observations were made for supercritical inlet operation and conditions of maximum total-pressure recovery.
Date: November 13, 1952
Creator: Connors, James F. & Woollett, Richard R.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Longitudinal Control Characteristics of a Wing-Tip Control Surface on a Sweptback Wing at Transonic Speeds by the NACA Wing-Flow Method

Description: Report presenting an investigation of the longitudinal control effectiveness of a full-chord wing-tip control surface on a wing with 35 degrees of sweepback, 12 percent thickness perpendicular to the quarter-chord line, an aspect ratio of 3.01, and a taper ratio of 0.605 at a range of Mach numbers. Wing-tip control was only 1/6 as effect in producing pitching moment at subsonic speeds as a flap type control and 1/2 as effect at low-supersonic speeds.
Date: June 13, 1952
Creator: Trant, James P., Jr.
Partner: UNT Libraries Government Documents Department
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An Investigation at Mach Numbers 2.98 and 2.18 of Axially Symmetric Free-Jet Diffusion with a Ram-Jet Engine

Description: "An investigation was conducted to determine the effectiveness of a free-jet diffuser in reducing the over-all pressure ratios required to operate a free jet with a large air-breathing engine as a test vehicle. Efficient operation of the free jet was determined with and without the considerations required for producing suitable engine-inlet flow conditions. A minimum operating pressure ration of 5.5 was attained with a ratio of nozzle-exit to engine-inlet area of 1.85" (p. 1).
Date: February 13, 1952
Creator: Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department
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Analytical and experimental investigation of inlet-engine matching for turbojet-powered aircraft at Mach numbers up to 2.0

Description: An analysis of inlet-turbojet-engine matching for a range of Mach numbers up to 2.0 indicates large performance penalties when fixed-geometry inlets are used. Use of variable-geometry inlets, however, nearly eliminates th The analysis was confirmed experimentally by investigating at Mach numbers of 0, 0.63, and 1.5 to 2.0 two single oblique-shock-type inlets of different compression-ramp angles, which simulated a variable-geometry configuration. The experimental investigation indicated that tot… more
Date: February 13, 1952
Creator: Schueller, Carl F. & Esenwein, Fred T.
Partner: UNT Libraries Government Documents Department
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Transonic free-flight investigation of the total drag and of the component drags (cowl pressure, additive, base, friction, and internal) encountered by a 16-inch-diameter ram-jet engine for Mach numbers from 0.80 to 1.43

Description: Report presenting an investigation of the drag on four full-scale models of 16-inch-diameter ramjet engines. The total, base, internal, and external drag were evaluated for each of the models. Results regarding the drag evaluations and drag comparison are provided.
Date: August 13, 1952
Creator: Messing, Wesley E. & Rabb, Leonard
Partner: UNT Libraries Government Documents Department
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