Report presenting a bibliography on atomic transition probabilities. The papers are arranged according to elements and stages of ionization, and the method employed and class of transitions are indicated behind each reference. Only articles on discrete transitions, both permitted and forbidden, are listed. Also included is a supplementary list of papers dealing with transition probabilities from a general point of view, a table showing the availability of numerical material on the individual atoms and ions, and a table of conversion factors.

"Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss" (p. 1).

Report presenting two blending equations that have been derived from an analysis based on certain assumptions relative to the cause of fuel knock. The main purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends.

"The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends. Two blending equations have been derived from an analysis based on certain assumptions relative to the cause of fuel knock" (p. 1).

Report detailing an investigation of the aerodynamic characteristics of a wing-propeller combination with the propeller rotating in the wing-chord plane of a two-dimensional wing. Total static lift was measured with and without the wing for a 3-foot-diameter propeller, while the effects of a ground plane on the static lift of the wing-propeller combination were measured with a 2-foot-diameter propeller. Results regarding static testing, forward speed tests, and propeller loads are provided.

Report presenting testing of a five-stage rocket-propelled model flown to a Mach number of 15.5 and an altitude of 98,200 feet. Temperatures were measured at six stations along the inside surface of the blunted conical nose with a total angle of 29 degrees. Experimental and theoretical values were similar at the first temperature measuring station, but the experimental results became increasingly greater than the theoretical values at rearward measuring stations.

Report presenting an investigation of transpiration cooling in a preflight jet model consisting of a double wedge of 40 degrees included angle with a porous stainless-steel specimen inserted flush with the top surface of the wedge. Nitrogen and helium were used as coolants and testing was conducted for flow rates ranging from about 0.03 to 0.30 percent of the local weight flow. The helium coolant required only about one-fourth to one-fifth the coolant flow weight as the nitrogen coolant for the same amount of heat-transfer reduction.

Report presenting a free-flight investigation of the zero-lift rolling effectiveness of air-jet spoilers on an unswept flexible wing over a range of Mach numbers. Testing was made to determine the relative effectiveness of air-jet spoilers at leading-edge and trailing-edge locations. The leading-edge jet spoiler exhibited near-zero effectiveness at transonic speeds and had a roll reversal between Mach numbers 0.93 and 1.35.

Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.

"This report presents the results obtained from pressure distribution tests on the fuselage of a PW-9 pursuit airplane in a number of conditions of flight. The investigation was made to determine the contribution of the fuselage to the total lift in conditions considered critical for the wing structure, and also to determine whether the fuselage loads acting simultaneously with the maximum tail loads were of such a character as to be of concern with respect to the structural design of other parts of the airplane. The results show that the contribution of the fuselage toward the total lift is small on this airplane" (p. 327).

"Full-scale aircraft crashes were made to investigate the mechanism of the start and development of aircraft crash fires. The results are discussed herein. This investigation revealed the characteristics of the ignition sources, the manner in which the combustibles spread, the mechanism of the union of the combustibles and ignition sources, and the pertinent factors governing the development of a crash fire as observed in this program" (p. 547).

Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.

This report follows the hydrogeochemical and stream-sediment study in the Cave Valley Basin, Nevada, conducted by the Lawrence Livermore Laboratory. This report contains only the analytical data and sample locations.

This report follows the hydrogeochemical and stream-sediment study in the Winnemucca Dry Lake Basin in Nevada that was conducted by the Lawrence Livermore Laboratory. This report contains only the analytical data and sample locations.

"Scale-up work on high temperature fuel recovery processes has progressed to the point where the (high temperature) vacuum furnace for several operations to the hot cells has been completed and tested under operating conditions. Small scale experiments on high temperature methods for processing molten irradiated uranium fuel have been made with spent X-10 fuel slug pieces. The results of direct Pu evaporation, treatment with fused fluorides and oxide scavenging were every similar to those found with tracer experiments."

"Engineering pertinent to the development of the sodium-cooled, graphite-moderated type of reactor was continued. This included work on problems related to the zirconium canned moderator, low enrichment uranium fuel, sodium piping, secondary coolant system, shielding, and the control and safety elements. A large fraction of the work was devoted specifically to problems of the proposed Sodium Reactor Experiment (SRE) configuration. In this connection, an integrated effort was initiated to prepare a complete preliminary design of the SRE by an early date. In addition, two alternate sodium-graphite reactor configurations were studied. One was an intermediate size, 145 thermal megawatt, unit optimized for the production of low cost plutonium. The second was a low power 10 thermal megawatt intended for power production, but in which sodium circulation through the core was entirely dependent upon thermal convection."

Report documenting the suitability of Mississippi for plant locations to produce synthetic liquid fuels, based on raw materials, water sources, and local interest.

An Alpha Scintillation Probe for use with the HAPO Cart Poppies has been designed to replace the air proportional probes presently used. The new probe has an average geometry of about 15 or 16 percent over an effective probe area of 23.4 in². Stability of operation under normal conditions of vibrations, humidity and temperature are inherent qualities and the average background count is stable at about two counts per minute. The high voltage used is in the order of 1,200 to 1,250 volts with a current requirement of 100 microamperes.

The surfaces of cold rolled, half hard, nitric acid treated, autoclave etched, 2S aluminum coupons were studied by optical and electronoscopic methods, before and after exposure to hot water alone and hot water and neutron bombardment. The non-exposed aluminum surfaces have a characteristic pattern which is absent in the exposed coupons. All of the exposed coupons were corroded. In general the coupons exposed to the higher flux intensities of irradiation were more severely corroded than those exposed to the lower flux intensities of irradiation or to the hot water alone. Representative photo-and electron micrographs illustrate the various types of surface structure observed on the control and experimental coupons.

"Recent theoretical advances in describing the nucleon-nucleon interaction (particularly in the T=1 state) have emphasized the importance of obtaining an unambiguous experimental determination of the scattering matrix so that the nuclear phase shifts and details of the nuclear potential may be revealed. It is possible to select five experiments, the results of which, in principle at least, determine the scattering matrix and phase shifts uniquely at one energy. Two of these experiments, the cross section and polarization over the angular range of 0 to 90 degrees in the center of mass system, have been made at the University of Rochester at a laboratory energy of about 210 Nev."

This memorandum is an outline of the principles and methods employed by 5100 Human Engineering Personnel in consultation on test equipment panel layout. The process of control panel layout is partially formalized with particular emphasis on test equipment panels. An experimental method is proposed for selecting an optimum panel layout. The essential role of experimentation is pointed out. The optimal layout for a nonrepetitive procedure is deduced and generalized to give methods of layout solution for the general repetitive procedure.