From abstract: "A method for fabricating 30-in.-long stainless steel - uranium dioxide sheet was developed and the properties of the fabricated sheet were investigated."

Abstract: "The cross section for the reaction Al²⁷(p,3pn)Na²⁴ has been measured for proton energies between 30 and 350 Mev relative to the cross section for the reaction C12(p,3pn)C11, and the absolute magnitude determined by matching with data measured with a Faraday cup at 350 Mev and at 31.5 Mev."

Studies in the 321 Building dissolver during December 1953 and January 1954, were successful in developing a laboratory-proved mercury-catalyzed dissolving flowsheet into a suitable plant procedure. However, this flowsheet was not adapted for Redox plant operation because of uncertainty about the possible presence of hydrogen above the lower explosive limit in the off-gases. Subsequent laboratory work has resulted in a better understanding of the hydrogen evolution, and has resulted in developing low hydrogen evolution flowsheets. When one of these flowsheets is selected for further work, it will be tested in the 321 Building dissolver with non-irradiated slugs to provide information for scaling-up the single-slug laboratory data to a plant-scale operation. It is the purpose of this memorandum to outline the factors considered to be pertinent to the 321 Building investigation, to be used as a guide in making preparations for the runs to be performed.

Letter opinion issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification; Commission of a County Tax Assessor-Collector for assessing and collecting delinquent taxes for a rural high school.

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, John Ben Shepperd, regarding a legal question submitted for clarification: Legality and effect of various provisions in a term life insurance policy issued under the wholesale plan.

Results of preliminary tests with photographic emulsions using a lip target are discussed. Some methods for the search of heavy mesons are suggested. The preliminary tests with photographic emulsions were designed to investigate exposure conditions inside the Bevatron. These were carried out with stationary targets, since injected targets were not available at that time. The first exposure was designed to study the shielding required for emulsions placed in the direct beam (9 inches from the magnet conterline) during the entire acceleration cycle. Three 200{micro} Ilford G5 emulsions embedded in various thicknesses of brass were exposed for 30 pulses. Nominal maximum energy of beam was 3.5 Bev. During the second and third exposure (nominal maximum beam energies 4.1 and 6 Bev respectively) a lip target was placed in front of the emulsions. This was designed so as to dampen out the radial oscillations in the first section (.36 inches thick, 1/2 inch radial length). The beam should then hit the second section (.9 inches thick, .75 inch radial length) which is designed to reduce the beam orbit by {approx} 1 1/4 inches and then hit the emulsions on the next turn. 1/2 inch brass absorber was placed ahead of the emulsions.

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Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Two groups of fixed-geometry nozzles and shroud combinations simulating double-iris-type configurations were evaluated over a range of secondary to primary exit-diameter ratios.

Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.

Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.

Sea-level static testing of turbojet engine afterburner.

From Introduction: "The investigation reported herein is a continuation of a ram-jet-combustor design program being conducted at the NACA Lewis laboratory. The purpose of this broad program is to establish basic design criteria for combustors operating over wide range of fuel-air ratio with low pressure losses and high combustion efficiency, and to utilize these design criteria in the development of practical ram-jet combustors."

From Summary: "Modifications A and B of impeller model MFI-1 and A, B, and C of impeller model MFI-2 were investigated experimentally in an attempt to determine what allowance in blade height should be made for boundary layer and viscous losses in an impeller designed for isentropic compressible flow. A gradual increase in blade height was arbitrarily made from inlet to outlet in anticipation of a gradual build-up of boundary layer. Apparently there was a rapid build-up of boundary layer near the inlet in the experimental case rather than a gradual one. Therefore, the proper allowance for boundary layer cannot be described from the data obtained."

From Summary: "Data obtained from the NACA air-launched ram-jet program are summarized with emphasis placed upon the transonic propulsive thrust potential of the engines. Data are presented for boosted and non-boosted engine configurations which incorporate a single-oblique-shock or double-oblique-shock diffuser designed for critical inlet operation at flight Mach numbers of 1.8 and 2.4, respectively. The engines are evaluated in terms of flight Mach number, mass-flow ratio, diffuser pressure recovery, combustion-chamber heat release, propulsive thrust, external drag, and specific impulse. From specific impulse considerations, it appears that for some air-launched missile applications the self-accelerating supersonic ram jet may have a lower gross weight than a rocket-boosted ram jet."

Report presenting a low-speed investigation to determine the lateral static and rotary derivatives of a model of a high-speed fighter airplane. The purpose was to compare experimental stability derivatives with derivatives estimated for a wing-fuselage combination, a vertical- and horizontal-tail combination, and a complete model.

From Summary: "An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-gas temperatures on the external and internal characteristics of a convergent-divergent nozzle having an area expansion ratio of 1.83. Data were obtained over a pressure-ratio range from 1 to 20 at free-stream Mach numbers of 1.6 and 2.0 for exhaust temperatures of 860 degrees, 1650 degrees, and 2000 degrees R. Results of this investigation indicated that generally both the internal and external performance characteristics were only slightly affected by a large change in jet temperature. The small differences in performance which did occur were predicted satisfactorily from theoretical considerations."

From Summary: "An experimental investigation was made to determine the feasibility of using hollow turbine blades in engines designed for short service life. Airfoils were fabricated from sheet material and techniques of welding and brazing attachment were investigated. The airfoils were not intended to be cooled. A principal objective was the reduction of strategic material requirements primarily as a function of direct weight reduction."

Report presenting an investigation in the 8- by 6-foot supersonic wind tunnel to evaluate the performance of a translating-cone inlet operated over a range of Mach numbers and angles of attack. The effects of spike projection and internal flow area variation on pressure recovery, external drag, and corrected air-flow variation were determined.

Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.

An investigation was conducted to determine the combustion response to rapid fuel-flow changes in a single tubular combustor at two simulated altitude-rotor speed conditions of 25,000 feet-70 percent rated engine speed and 50,000 feet-70 percent rated engine speed. Limiting rates of change of fuel flow (acceleration limits) were determined and the effects of certain combustion air flow variables on the transient combustion characteristics were studied with the aid of rapid-response instrumentation.

Report presenting an analysis of results obtained from a transonic wind-tunnel investigation of two bodies of revolution with the same nose shape but two different shapes of afterbody. Results regarding pressure distribution, normal-force characteristics, pitching-moment and center-of-pressure characteristics, and detailed load characteristics are provided.

A study of a series of three single-passage nozzles, designed to turn the flow at different velocity levels but to identical outlet conditions, in order to determine whether secondary-flow accumulations of boundary-layer fluids within nozzles could be minimized by use of low-velocity turning. Results indicated that the type of turning with subsequent acceleration is highly effective in minimizing secondary-flow accumulations at the corner where the suction surface joins the end walls.

Memorandum presenting a calculation of theoretical values of rocket performance parameters for JP-4 fuel and various mixtures of liquid fluorine and liquid oxygen, assuming equilibrium and frozen composition during the expansion process. Data were calculated at several equivalence ratios for each assigned fluorine-oxygen mixture. Some of the parameters explored include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area.

Report presenting an experimental investigation of the performance capabilities of an asymmetric swept nose inlet of circular projection in the supersonic wind tunnel at a Mach number of 3.85. The aysmmetric inlet was evaluated in terms of its pressure recovery and mass-flow characteristics for angles of attack up to 9 degrees. Results regarding diffuser performance, supercritical flow patterns, oblique shocks, subcritical stability ranges, and Mach number profiles are provided.