This dataset contains the first part of field data on the study of hydrogeochemical and stream sediments from the Pratt quadrangle, Kansas.

Part two of field data for hydrogeochemical and stream sediment studies made in the Pratt quadrangle, Kansas.

This technical report describes a pulse height converter that employs the R.F. vernier method. This particular converter has been developed for use with the pulsed beam facility of the BNL Van de Graaff. This report then details a number of tests of the converter made using a RIDL model 34-12, 400-channel analyzer. The report includes 6 figures and 4 circuit diagrams to accompany the findings.

Experimental work concerned with the development of an inexpensive composite fuel plate with a high burnup potential for application in a 500°C sodium environment as Core B of the Enrico Fermi Fast Breeder Reactor.

The majority of two-phase flow problems involving equations of state are solved by use of point-wise utilization steam table values. In this manner, problems involving the use of the various flow equations of continuity, momentum and energy are generally forced into iterative solutions. Considerable effort towards the development of an analytical expression for the state equation seems indicated so as to simplify the analysis of two-phase problems, particularly the transient cases. The question of instability of state and mixture condition is particularly apparent in the analysis of systems undergoing phase transformation as demonstrated by the significant difference between simple theory and experimental critical flow determinations. The assumption of homogeneous, equilibrium mixtures is indicated as a first attack upon the problem.

Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.

"A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).

Report presenting testing on six blunt-nose models at angles of attack ranging from 0 to 5 degrees in order to evaluate the heat transfer and pressure on their surfaces. Information about transition, proper design, and locations of greatest and least heat transfer is provided.

"Measurements of aerodynamic heat transfer have been made along the hemisphere and cylinder of a hemisphere-cylinder rocket-propelled model in free flight up to a Mach number of 3.88. The test Reynolds number based on free-stream condition and diameter of model covered a range from 2.69 x l0(exp 6) to 11.70 x 10(exp 6). Laminar, transitional, and turbulent heat-transfer coefficients were obtained" (p. 1).

Report presenting testing of four models of a thin magnesium fin, with the leading edge swept back 35 degrees, of a type used to stabilize the first stages of rocket-propelled multistage hypersonic models. The investigation was carried out to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective methods. The fins tested included a basic fin, a fin with a blunt leading edge, a fin with a blunt leading edge wrapped with Inconel, and a fin with a blunt leading edge made of stainless steel.

From Introduction: "The use of automatic controls to reduce the tendency for rolling divergence has been investigated in references 2 and 3. These studies have considered the effect of artificial changes in certain stability derivatives on the rolling divergence, and have shown that increased damping in pitch may be quite effective in reducing the divergent tendency. In the present report, a different type of automatic control is investigated."

Report presenting force-test data showing the effects of change in leading-edge radius on the low-speed longitudinal stability of a 6-percent-thick 45 degree sweptback wing of aspect ratio 3 for several ranges of Mach and Reynolds numbers. The results indicated that as the airfoil sections were thinned at the nose, separation effects occurred at lower values of lift coefficient.

Report presenting a theoretical investigation to determine the static and dynamic characteristics of a control-surface actuator and missile combination, with primary consideration given to the minimization of the effects of Mach number and altitude.The results indicate that the type of actuator studied in combination with a missile might replace a gain-adjusted acceleration control system. Results regarding the control-system static characteristics, control-system dynamic characteristics, comparison of torposervo and position-servo actuation, and some suggestions for further research are provided.

Report presenting flight measurements of the horizontal-tail loads on the Douglas X-3 research airplane during wind-up turns, pull-ups, and stabilizer pulses over a range of altitudes and Mach numbers.

A metallurgical examination of several resistance thermometers for 105-KW were examined before startup (1). This examination revealed that the silver brazes joining the type 305 stainless steel blades to the type 416 stainless steel nuts were defective. The braze metal did not penetrate into the joint; the brazes were porous and appeared to be inadequately bonded to the type 416 nuts. After startup of KW, many of the thermometers became inoperative, and several were visually examined to determine the integrity of the units. The presence of corrosion products at the junction of the braze and the nut led to further metallurgical examination of the brazed joints. Twenty units from 105-KW, 12 prototype units from 105-H, and two "new model" units were included in this examination. The examination was conducted to determine the cause and nature of the failures observed on units under service conditions.

Introduction: This is the fifth of a series of reports covering technical progress on the research and development program being performed in connection with the design of the Pathfinder Atomic Power Plant.

A resume of process development studies conducted with Lukachukai ores is presented. Data for the following phases of the work are reported in detail: 1. Roasting and leaching of uranium leach residues, and, 2. Uranium ion exchange. Other phases of the work are discussed and references cited.

Report presenting testing of a parabolic body of revolution in the 4- by 4-foot supersonic tunnel at two Mach numbers. The investigation included the effects of Reynolds number, fins, internal contour of body base, and two support systems on body pressure and force drag at an angle of attack of 0 degrees.

Report discussing progress in research and development by the Health Instrument Divisions, Hanford Works, for the term from January through March, 1951.

The following report follows an investigation comparing "staggered" and "spit-flow" air cooling systems.

A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eight radial stations of the NACA 10-(5)(066)-03 propeller.

A theoretical analysis of the temperature distribution through the trailing portion of a blade near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the hot spot temperatures at the trailing edge and influence of design variables. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.

Abstract. Irradiated Whiting graphite possesses a small negative or a positive Hall constant, depending upon the dosage. Annealing at 500 degrees C for 1 hour in helium results in a Hall constant which is large in magnitude and negative in sign. The properties of the annealed graphite are presumably close to those of the original unirradiated material. Unirradiated AGOT-K graphite has a large, negative Hall constant. A mechanism is suggested which accounts for the change in sign of the Hall constant as a result of neutron bombardment.

A report regarding the San Miguel River District, San Miguel Plateau Area, colorado.