Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.

This document provides a summary of facilities, both proposed and constructed, and programs of the Hanford Atomic Products Operation. Budgets, by program, are also provided. (FI)

This report addresses the constant-pressure leak rate gage.

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Property changes in polycrystalline graphite resulting from reactor irradiations at temperatures up to 185 deg C and over a range of exposures up to 1135 Mwd/ CT have been determined. Changes in stored energy, thermal conductivity, sample length, and C/sub O/ interlayer crystallite spacing are markedly decreased as exposure temperature is increased. Electrical resistivity changes are also less at higher exposure temperatures, but this property change does not depend as strongly on temperature as the others. Isothermal annealing studies of C/sub O/ changes were conducted on a number of irradiated samples. The data were analyzed assuming a large number of processes distributed in activation energy. The results are summarized in activation energy spectra in which the distribution of C/sub O/ damage is given as a function of the activation energy required for annealing. It is found that not only does a higher exposure temperature decrease the total amount of property change, but also the distributlon of damage accumulated is considerably different. Results are discussed in terms of the radiation damage model suggested by Hennig and Hove. This model is compatible with the experimental results presented. (auth)

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Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.

Memorandum presenting an investigation to determine the internal flow performance of a fixed 14 degree ramp inlet from zero to 20 degrees angle of attack conducted at three free-stream Mach numbers. The inlet was mounted in three circumferential fuselage locations and utilized inlet throat and fuselage boundary-layer removal.

Memorandum presenting a wing-root inlet configuration in which inlet components were varied and was tested in the 4- by 4-foot supersonic pressure tunnel at 3 Mach numbers. Angles of attack and sideslip ranges were also varied. Inlet performance and engine-flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed.

Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.

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Design criteria and operating experience with the aluminum oxide bearing and journal combination as installed in canned rotor pumps in in-pile loops are described. No pump failures occurred in 8 pumps with A1/sub 2/0/sub 3/ bearings over a cumulative period of l0,000 hours due to wear or corrosion. Five failures due to slippage and/or electrical breakdown of the stator insulation are reported. (T.R.H.)

Review of ThO/sub 2/ caking and sphere forming experiences in the 200 and 100 gpm loops shows that cakes and spheres always formed in the first 100 hours of the run or did not form at all, suggesting that processes in addition to oxide particle degradation were present. Many ThO/sub 2/ circulation tests in which no major difficulties were experienced suggest that preparation of oxides suitable for reactor use may have been accomplished, at least insofar as the caking problem is concerned. Further research is required to distinguish between oxide preparations. Evaluation of ThO/sub 2/ batches by cake resuspension index'' studies are described. A qualitative indication of the caking tendency of various batches of ThO/sub 2/ is given. Observations of ThO/sub 2/ sphere growth in stirred systems at atmospheric pressure indicate that added electrolytes have a strong influence. The results of ThO/sub 2/ cake disintegration tests are reviewed. A cake disintegration method has been used successfully twice to remove hard cake from inaccessible points in loops. The proposed program for caking studies in the 30 gpm loop, which is under construction, is outlined. The potential usefulness of several avenues for investigation of ThO/sub 2/ surface chemistry is indicated and the …

Report issued by the Oak Ridge National Laboratory discussing annual progress made by the Solid State Division. Work and research progress made during 1957 is presented. This report includes tables, illustrations, and photographs.

Report issued by the Brookhaven National Laboratory discussing methods of processing reactor fuels such as uranium. As stated in the objective, "the primary objective of the project was to determine the effect of temperature, solution composition, and flow rate on the dissolving time for natural uranium slugs of varying history" (p. 2). This report includes tables, illustrations, and photographs.

Report presenting a transonic investigation in the 16-foot transonic tunnel to determine the effects of spanwise location of a flap-type aileron on the lateral characteristics of a 4-percent-thick sweptback-wing-fuselage model. Results regarding the effect of aileron spanwise position on roll and lift effectiveness, tail effects, and effect of spanwise aileron position on complete model rolling-moment characteristics are provided.

Report presenting the lift and drag characteristics of a 60 degree delta-wing interceptor airplane with a fuselage extension and indentation. The data was obtained over a range of Mach numbers and altitudes. Results regarding a comparison with a prototype airplane with similar wings and a comparison of the flight tests with model tests are provided.

Memorandum presenting a seven-part investigation of hydrogen for turbojet and ramjet powered flight. The combustion characteristics of hydrogen, in ramjets and afterburners, and in turbojet engines are described.

Report presenting an improved air-cooled turbine blade that was described, stress-analyzed, and evaluated in a full-scale turbojet engine. The blade consists of a sheet-metal outer shell and an internal strut of partial blade length. The effect on blade rupture life of varying outer-shell thickness, strut length, blade temperature distribution, and corrugation pitch and amplitude are provided.

Report presenting an investigation of resistance screens for the purpose of obtaining uniform flow in ducts. The new screen designs consisted of several different screen shapes with the elements set at oblique angles (swept) to the flow. Results regarding a rectangular channel and diffuser investigation are provided.

Report presenting the aerodynamic load characteristics for a wing-body combination for a range of Mach numbers and angles of attack. Two wings with the same dimensions but different types of construction (one of solid steel, one of plastic with an inner steel core) were tested. Results regarding flow studies, chordwise pressure distributions, spanwise load distributions, panel loads, center of loads, and twist distribution are provided.

Report presenting an investigation to determine and improve on the foreign-object-retention capabilities and pressure-loss characteristics of rectractable engine-inlet screens. Testing occurred with two commerically made retractable screens installed in the engine-inlet sections for which they were designed. Results regarding the retention for both the original and modified screens and pressure tests are provided.