Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.

Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.

Report presenting wind-tunnel testing of submerged air inlets on the fuselage of a scale model of a typical fighter-type airplane. The results are presented for ramp plan forms with parallel and with diverging walls and show the effect of the duct-entrance location, internal ducting efficiency, and deflectors.

Memorandum presenting wind-tunnel tests of a semispan model of an unswept wing of aspect ratio 4 and taper ratio 0.5 at Mach numbers up to 0.94 to determine its aerodynamic characteristics as influenced by Mach number, Reynolds number, and modification of the basic diamond profile by rounding the ridge. Lift, drag, and pitching-moment data are presented for a range of Reynolds and Mach numbers. The results indicated that no severe static-longitudinal-stability problems up to Mach number 0.94.

Report presenting an investigation of an air-cooled internal-strut-supported blade in a modified production turbojet engine to determine the cooling effectiveness of this type of blade and the cooling-air pressure loss through the blade under engine operating conditions. Experimental results are presented and compared with the results of an analytical investigation.

Memorandum presenting an investigation of the static aerodynamic and dynamic damping-in-roll characteristics of an aircraft rocket with cruciform fins of trapezoidal plan form as determined experimentally at a range of Mach numbers. The fins had tow holes cut through each fin panel, and the effects of the holes or slots were investigated by testing with both solid and slotted fins.

"In order to understand the operation and the interaction of jet-engine components during engine operation and to determine how component characteristics may be used to compute engine performance, a method to analyze and to estimate performance of such engines was devised and applied to the study of the characteristics of a research turbojet engine built for this investigation. An attempt was made to correlate turbine performance obtained from engine experiments with that obtained by the simpler procedure of separately calibrating the turbine with cold air as a driving fluid in order to investigate the applicability of component calibration. The system of analysis was also applied to prediction of the engine and component performance with assumed modifications of the burner and bearing characteristics, to prediction of component and engine operation during engine acceleration, and to estimates of the performance of the engine and the components when the exhaust gas was used to drive a power turbine" (p. 1).

From abstract: "This progress report describes four IBM 704 codes developed and used by UCRL, Livermore, to investigate the motion of any object in the force fields of the sun and any or all of the planets and their satellites."

By using a large central fuel and blanket reprocessing facility, slurry-fueled aqueous homogeneous reactors can attain an estimated minimum fuel cycle cost of 1.4-1.6 mills/kwh; with solution-fueled two-region reactors, a doubling time of 14 years may be obtained at a fuel cycle cost of 2.0 mills/kwh. On-site processing appears desirable only for large power stations made up of reactors designed for short doubling times. For instance, a solution-fueled two-region reactor can attain a 12-year doubling time at an estimated fuel cycle cost of 1.5 mills/kwh at a 2000 Mw electricity station with an on-site processing plant.

A method was developed for the spectrophotometric determination of 30 to 100 ug of osmium as OSO4 is extracted with CHCl3 and diphenylcarbazide is then added to the organic extract. A blue-violet reaction product is formed, the absorbancy of which is measured at 560 mu. A suitable reagent concentration is from 3 to 5 ml of 0.2% diphenylcarbazide in a volume of 25 ml and the preferred solvent for the reagent is ethanol. Beer's law is followed over a range of 8 to 130 ug of osmium with a coefficient of variation of about 4%. After a 2-hour color-development period the molar absorbancy in less than 2 hours were unsuccessful. A study was made of the effects of foreign elements and only Ru(VIII) was found to interfere.

This document reports a preliminary airborne reconnaissance survey that was conducted in the mountain ranges of the northwest portion of Nevada.

The ORIC (Oak Ridge Relativistic Isochronous Cyclotron) radiofrequency system for which Model III represents the resonator is the third system which has received enough consideration to warrant construction of a model. The purpose of the model is to check the calculations for the frequency range and excitation power of the resonator. After an introductory description of the r-f system and model, the detailed calculations of the properties of the model will be given followed by the data from measurements of the model characteristics.

The feasibility of using electroless nickel, a chemical deposit containing about 10 wt% phosphorous in nickel, as the brazing alloy for assembling tubular stainless steel fuel elements of the type specified in Core I of the N. S. Savannah was investigated. This material was nelected primarily because of the case of braze-metal preplacement by chemical deposition of the alloy on type 304 stainless steel ferrule spacers, prior to fuel-bundle assembly. Brazed joints produced by this method were generally characterized by a relatively ductile solid-solution region at the thinnest portions of the fillet. This ductile zone should minimize the possibility of complete propagation of hairline cracks, which form in the brittle, eutectic regions of fillet.

The development of swaging and vibratory compaction process for fabrication of clad UO2 fuel rods is described. The cost is less than 50% of that for an equivalent core fabricated from pellets. The irradiation testing of vibratory filled and swaged UO2 rods is reported for burn-ups from 2,000 to 12,000 Mwd/t UO2; the results indicate that the rods are capable of excellent performance power reactors.

Abstract: A cyclic stress analysis of the SM-1 primary system was carried out. Problems encountered in the fabrication of PM-2A Core II and SM-lA Core II are described, and the results of an examination of damaged SM-lA Core I stationary fuel elements reported. A preliminary study of the radiation damage to SM-1 reactor vessel was made and the possibility of annealing the vessel discussed. Performance analyses are presented for five cores: SM-1 Core, SM-1 Core 1 rearranged and spiked, SM-1 Core II with special components, PM-2A Core 1, and SM- 1A Core 1. Preliminary critical experiments were made with SM-2 elements in a SM- 1 core configuration and nuclear and thermal analyses of the use of SM-2 elements in SM-1, SM-1A, and PM-2A completed. A throttling steam calorimeter was selected for measuring moisture carry-over on the PM-2A steam generator. Test procedures for evaluating the shielding of the SM-1, SM-lA, and PM-2A plants are summarized. Radiochemical and chemical analyses of SM-1 coolant and crud are summarized, and methods of activity control discussed. Preliminary results of studies of the properties of reactor pressure vessels under irradiation and no irradiation conditions are summarized briefly.

(p,xp) reactions are those nuclear reactions induced by high energy protons in which both the mans and the charge of the target nucleus are reduced by x-1 units. The most common type of these reactions to be expected in the 100 to 400 Mev region involves the exclusive emission of protons as a results of the interactions. The specific (p,xp) reactions investigated in this study were those where 2 is less than or equal to x where x is less than or equal to 5.

Report describing the thermal hydraulics facilities at Hanford Laboratories as well as its operation, equipment, and systems.

Experimental combination hand and shoe counter redesign as a compact, simplified, register readout instrument no larger than the present Five-Fold called Model 2.

"A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage and stub horizontal tail was tested in the Langley stability tunnel to determine the aerodynamic characteristics of the model, The investigation included a study of the effects of boundary layer thickness, rudder area, and cover-plate alinement on the aerodynamic characteristics. Tuft studies were made in the vicinity of the junction of the vertical and stub horizontal tails" (p. 1).

Report presents the results of a comprehensive experimental study carried out at full scale in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the functioning of the power plant and propeller unit under different conditions. This report deals particularly with the problem of the cooling of an airplane engines on the ground. The influence of different nose forms, skirts, flaps, propellers, spinners, and special blowers has been investigated.

This report gives the theoretical distribution of pressure at lift coefficients of 0, 0.5, 1.0, and 1.5 for 20 airfoils, calculated on the basis of a rigorous potential theory of arbitrary airfoils. It also provides tables from which the characteristics of the airfoils for any angle of attack in 2-dimensional potential flow are readily calculable. The theoretical values of the angles of zero lift, the lift and moment coefficients, and the ideal angles of attack are listed and some comparisons with experiment are indicated. The results presented may be of value in predicting structural loads and also in a correlation of theoretical pressure gradients with profile resistance.

"An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.00. Considerable difficulty was experienced in attempting to establish or maintain balanced-cycle engine operation at altitudes above 36,000 feet" (p. 1).

A report discussing an exploration of the san Miguel Bench

Documentation outlining characteristics of field data samples taken in the Tascotal survey area portion of the detailed geochemical survey for Trans-Pecos, Texas.