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Low-Melting Alloys for Cast Fuel Elements

Description: The following report follows an investigation made to determine the composition of uranium-rich ternary eutectic alloys most suitable for reactor application in the as-cast condition. These determinations were made based metallographic examination and thermal analysis of as-cast alloys.
Date: May 19, 1955
Creator: Saller, Henry A.; Rough, Frank A. & Bauer, Arthur A.
Partner: UNT Libraries Government Documents Department
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The Disposal of Radioactive Wastes

Description: Technical report describing a brief survey of the problems concerned with radioactive waste disposal.
Date: June 19, 1955
Creator: Ophel, Ivan L.
Partner: UNT Libraries Government Documents Department
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Interim report - Production Test MR-105-12 crossheader purge with chromic acid

Description: The primary purpose of this test was to demonstrate that the inside of a rear-cross-header, its nozzles and pigtails could be decontaminated by recirculating for 30 minutes, a 60{degrees} C, O.3 pH chromic acid solution. Secondary purposes were, (1) to determine the magnitude of radiation increase in piping and acid equipment external to the reactor encountered during the test and (2) to obtain information as to the kind and amount of contaminants removed by the acid solution.
Date: September 19, 1955
Creator: Hardin, A. K.
Partner: UNT Libraries Government Documents Department
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The Theory of Isotope Separation by Countercurrent Chemical Exchange

Description: The theory of isotope separation by countercurrent chemical exchange is worked out in detail using the continuous transfer concept. A comparison is made with discrete stagewise processes such as gaseous diffusion and with various general concepts of solvent extraction. The effects of a cell structure in the flow system is also worked out. An elementary design procedure is included both for the no-loss case and the case where the losses are small. In addition, a method of estimating stage length… more
Date: January 19, 1955
Creator: E., DeMarcus W.C. & Von Halle
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds

Description: From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."
Date: July 19, 1955
Creator: Piland, Robert O. & Collie, Katherine A.
Partner: UNT Libraries Government Documents Department
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Some Effects of Fluid in Pylon-Mounted Tanks on Flutter

Description: Report presenting fluid-dynamics studies of a tank of fineness ratio 7.0 which was pylon mounted on a simplified two-dimensional flutter model in order to determine the effects of the fluid on flutter. The flutter speed was determined for three cases: with various amounts of water in the tank, with weights with the same mass and moment of inertia as the fluid considered to be a frozen solid, and with weights with the same mass and moment of inertia as the actual fluid. Results regarding the flu… more
Date: July 19, 1955
Creator: Reese, James R.
Partner: UNT Libraries Government Documents Department
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Rocket-engine throttling

Description: An investigation of the performance and operating characteristics of two variable-thrust injectors over a wide thrust range using mixed oxides of nitrogen and ammonia. Specific impulse, characteristic velocity, thrust coefficient, and overall efficiency are presented as functions of thrust. A maximum thrust range of 12 during one run was obtained with a triplet impinging-jet injector.
Date: December 19, 1955
Creator: Tomazic, William A.
Partner: UNT Libraries Government Documents Department
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Design procedure for transpiration-cooled strut-supported turbine rotor blades

Description: From Summary: "The procedure currently employed by the NACA Lewis Laboratory in the design of transpiration-cooled strut-supported turbine rotor blades is discussed. The strut is the internal blade supporting member and also serves to partition the blade into separate cooling-air passages. Orifices in the blade base, which meter the cooling-air to each internal passage, are used in conjunction with a constant chordwise permeability."
Date: December 19, 1955
Creator: Prasse, Ernst I. & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0

Description: Inserting a splitter plate in the subsonic diffuser caused a pressure-recovery loss of about 1 percent for an inlet with a long nearly constant-area throat section. The loss was due to the increased surface area. Another inlet, which had a comparatively rapid area increase immediately after the throat, experienced pressure-recovery losses of 5 and 6 percent at Mach numbers of 1.8 and 2.0, respectively, and about 1 percent at Mach 1.5.
Date: December 19, 1955
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
open access

Performance and Component Frontal Areas of a Hypothetical Two-Spool Turbojet Engine for Three Modes of Operation

Description: Engine performance is better for constant outer-spool mechanical-speed operation than for constant inner-spool mechanical-speed operation over most of the flight range considered. Combustor and afterburner frontal areas are about the same for the two modes. Engine performance for a mode characterized by a constant outer-spool equivalent speed over part of the flight range and a constant outer-spool mechanical speed over the rest of the flight range is better that that for constant outer-spool m… more
Date: December 19, 1955
Creator: Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
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A Study of the Correlation Between Flight and Wind-Tunnel Buffeting Loads

Description: Report presenting a comparison of the buffet loads measured on wind-tunnel models with loads measured in flight, which indicate that a simple strain-gage measurement can be used in wind tunnel testing that can be used to predict the wing buffet loads on the airplane. The technique appears to be usable for both unswept and swept configurations.
Date: July 19, 1955
Creator: Huston, Wilber B.; Rainey, A. Gerald & Baker, Thomas F.
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation at Mach number 1.9 of simulated wing-root inlets

Description: Report presenting an experimental investigation to study several wing-root inlet configurations at Mach number 1.9. The inlets were of triangular and rectangular shape and external compression was provided by two-dimensional wedge surfaces. Results regarding the pressure-recovery and mass-flow data, effect of inlet side plates and curved diffusers, exit and inlet total-pressure distributions, improvement of exit total-pressure profiles, and inlet tests at zero flight speed are provided.
Date: January 19, 1955
Creator: Piercy, Thomas G. & Weinstein, Maynard I.
Partner: UNT Libraries Government Documents Department
open access

Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design

Description: Report presenting an investigation at the Lewis laboratory to develop air-cooled, strut-supported turbine blades. Six blades were investigated in a full-scale turbojet engine to obtain data on blade durability and blade-cooling effectiveness and strut temperature. Results regarding the heat-transfer investigation and blade-durability investigation are provided.
Date: January 19, 1955
Creator: Schum, Eugene F.
Partner: UNT Libraries Government Documents Department
open access

Performance of YJ73-GE-3 turbojet engine in altitude test chamber

Description: Report presenting the steady-state performance of the YJ73-GE-3 turbojet engine in an altitude test chamber for a range of exhaust-nozzle areas, simulated altitudes, and Mach numbers. A method of performance calculation based on engine pumping characteristics is provided. Results regarding performance maps, pumping characteristics and performance prediction, thrust correlation, effect of inlet temperature on performance, calculated performance from pumping characteristics, and altitude-ignition… more
Date: January 19, 1955
Creator: Kaufman, Harold R. & Dobson, Wilbur F.
Partner: UNT Libraries Government Documents Department
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Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers

Description: Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limita… more
Date: January 19, 1955
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Partner: UNT Libraries Government Documents Department
open access

Turbojet engine investigation of effect of thermal shock induced by external water-spray cooling on turbine blades of five high-temperature alloys

Description: Report presenting an investigation of the thermal-shock effect of water-spray impingement upon turbine rotor blades subjected to rated engine operating conditions using external water-spray cooling. Turbine-blade cooling water was turned on and off in cycles which employed either sudden or gradual injection of cooling water. Results regarding blades modified and unmodified for rotating injection are provided.
Date: December 19, 1955
Creator: Freche, John C. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing

Description: "A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).
Date: January 19, 1955
Creator: Bowden, Dean T.
Partner: UNT Libraries Government Documents Department
open access

Effect of fuselage fences on the angle-of-attack supersonic performance of a top-inlet-fuselage configuration

Description: Report presenting an investigation of the effect of longitudinal body fences on the performance of a top-inlet-fuselage combination in the 8- by 6-foot supersonic wind tunnel. The investigation was conducted at a range of Mach numbers, angles of attack, and a range of inlet mass-flow ratios. The thrust-minus-drag of the top-inlet configuration with fences was higher than the bottom-inlet configuration without fences over most of the range, with the reverse being true at all lift coefficients at… more
Date: January 19, 1955
Creator: Kremzier, Emil J. & Campbell, Robert C.
Partner: UNT Libraries Government Documents Department
open access

Drag Investigation of a Swept-Wing Fighter-Airplane Model Incorporating Two Drag-Rise-Reducing Fuselage Revisions

Description: Report discussing several configurations of a swept-wing fighter airplane to determine the effects of modified applications of the transonic and supersonic area rules on the transonic drag-rise characteristics. Information about the lift and pitching-moment characteristics is also provided.
Date: July 19, 1955
Creator: Whitcomb, Charles F. & Lee, Edwin E., Jr.
Partner: UNT Libraries Government Documents Department
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