Report issued by the Bureau of Mines over investigations of coking coal reserves of Overton County, Tennessee. Testing to determine suitability for producing metallurgical coke is also presented. Methods used, and measurements of coal reserves are listed. This report includes tables, maps, and illustrations.

Report issued by the Bureau of Mines over development of systematic flooding in oil field reservoirs. As stated in the introduction, "this report presents a discussion of four full-scale water-flooding projects in the Delaware-Childers field and 1 pilot project in the Curl Creek field" (p. 1). This report includes tables, graphs, maps, and illustrations.

Abstract: "Aluminum-clad nickel-plated uranium is corrosion resistant in boiling water. Samples with intentional defects in the aluminum-nickel clodding layers, after testing for more than 300 hr. showed no sign of rapid failure. The study of electroplated metals on uranium for aluminum cladding has defined the effects of several processing variables on the corrosion resistance. The quality of the uranium and the quality of the aluminum-nickel bond were important. Heat treatment and vacuum outgassing of the nickel-plated uranium prior to aluminum cladding were beneficial, and minimizing the amount of air present in the hot-press assembly was desirable. Variation in the steps for electroplating on uranium did not affect the corrosion resistance of aluminum-clad uranium."

Introduction: "The uranium-5 w/o chromium alloy has been intensively investigated for use in a power reactor in the as-cast condition. However, when cast sample fuel elements were subjected to irradiation, their stability was found to be unsatisfactory. In order to improve the behavior of the alloy, a program of grain refinement by heat treatment was begun. The effect of chill casting on the heat-treated grain size was also investigated."

The following report follows an investigation made to determine the composition of uranium-rich ternary eutectic alloys most suitable for reactor application in the as-cast condition. These determinations were made based metallographic examination and thermal analysis of as-cast alloys.

From abstract: The uranium deposits of the Mayoworth area, Johnson County. Wyo., are in oolitic limestone at the base of the Sundance formation of Late Jurassic age. The uranium mineral has been identified as metatyuyamunite, a hydrous calcium uranium vanadate, that coats joints and fractures and replaces calcite in both the cement and the oolites. The known deposits of the area are of sub-ore grade, have a high lime content, and are not of economic importance at this time.

Abstract: "The shock-tube experiments of Professor R. G. Fowler and his co-workers at the University of Oklahoma, and of Professor Arthur Kantrowits and his group at Cornell University, are reported by the author, who visited the laboratories of the two groups. Fowler's group has studied expanding low-pressure sparks; Kantrowits and his group have studied shocks produced by the adiabatic expansion of a compressed gas."

Abstract: "A cylindrical coil has been designed for pulsed field operation suitable for use in a model thermonuclear reactor. The coil has an eight-inch inside diameter and a length of fifty-one inches. Magnetic mirrors at the ends consist of double-layer solenoids six and one-half inches long designed to slip over the main coil. Subsequent models of this coil have been fabricated which improved the electrical insulation provided by the bonding materials and the mechanical rigidity of the coil. Peak central fields of fifteen kilogauss and mirror fields of thirty kilogauss have been obtained."

From introduction: This report details the conceptual design of a 100 kw gas cooled reactor power plant of the type that would satisfy the electrical and space heating load of the Air Force distant early warning stations and might find application at other remote bases.

"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).

Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.

Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.

Report presenting a consideration of the problem of shaping an adjoining fuselage for a given wing and supersonic Mach number so that the combination will have a low wave drag. Only fuselages that can be simulated by singularities distributed along the body axis are studied.

Memorandum presenting the Bell X-5 research airplane tested at 58.7 degrees sweepback during the program to determine the characteristics of a variable-sweep fighter airplane at transonic speeds. This paper includes the stability and control characteristics in the stable lift range up to Mach numbers near 1.0 at an altitude of 40,000 feet and to slightly lower Mach numbers at altitudes of 25,000 feet and 15,000 feet. Results regarding general comments, static stability and control characteristics, and longitudinal dynamic stability are provided.

"The effects of interaction between a landing gear and a flexible airplane structure on the behavior of the landing gear and the loads in the structure have been studied by treating the equations of motion of the airplane and the landing gear as a coupled system. The landing gear is considered to have nonlinear characteristics typical of conventional gears, namely, velocity-squared damping, polytropic air-compression springing, and exponential tire force-deflection characteristics. For the case where only two modes of the structure are considered, an equivalent three-mass system is derived for representing the airplane and landing-gear combination, which may be used to simulate the effects of structural flexibility in jig drop tests of landing gears" (p. 619).

"A general matrix method is developed for the solution of characteristic-value problems of the type arising in many physical applications. The scheme employed is essentially that of Gauss and Seidel with appropriate modifications needed to make it applicable to characteristic-value problems. An iterative procedure produces a sequence of estimates to the answer; and extrapolation techniques, based upon previous behavior of iterants, are utilized in speeding convergence. Theoretically sound limits are placed on the magnitude of the extrapolation that may be tolerated" (p. 747).

Report presenting an investigation of the blades of an experimental two-blade jet-driven helicopter when subject to a condition of near resonance between the frequencies of the first elastic bending mode of the blades and third harmonic component of the aerodynamic loading that results in high bending strains in normal flight conditions. Various changes in design configuration on the blade bending strains were explored. Results regarding the preliminary studies, effects of variation in flight conditions and blade configuration, and harmonic analysis are provided.

Note presenting an experimental investigation of the heat-loss characteristics of heated fine wires suitable for use as anemometers in turbulence research. The effects of each of the several variables on the heat-loss characteristics of both normally oriented and swept wires were measured. The temperature-loading effects were found to cause large sensitivity differences between constant-temperature and constant-current operation.

Note presenting wind-tunnel tests to ascertain the total-pressure recovery of a circular nose inlet utilizing various shapes of inlet lips. The tests were conducted at a free-stream Mach number of 0.237 with inlet flows ranging from low values to choking and at angles of attack from 0 to 25 degrees.

Report presenting a free-flight test technique that can be used to obtain damping in roll of sting-mounted wings and wing-fuselage combinations over high subsonic, transonic, and supersonic speeds with rocket-propelled test vehicles. Results regarding delta wings and unswept tapered wings are provided.

Note presenting a new approach to the theory of the mixing of two currents in an injector which deals with an incompressible ideal fluid. The theory shows new potentialities in an appropriate shaping of the form of the walls of the mixing zone so as to improve the jet-syphon efficiency beyond the heretofore theoretically predicted. A few examples of ways to improve jet-syphon efficiency are indicated.

Report presenting an investigation to determine the shear strengths of high-temperature-alloy blazed joints. The variables investigated included the method of brazing, nickel addition to the brazing alloy, brazing temperature, holding time at temperature, and a protective coating on the braze area for salt-bath specimens. Results regarding individual phases and the microstructure of brazed joints are provided.

From Introduction: "Most of the existing analyses for turbulent flow and heat transfer in passages have been confined to circular tubes or parallel plates (refs. 1 to 5). In reference 6, temperature distributions for rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients. Some work on the calculation of the velocity and shear-stress distributions in corners is reported in reference 7."

Note presenting an investigation of screens placed transversely across the jet as a noise-reduction device on a full-scale turbojet engine to determine the effect on the sound field of screen mesh, wire diameter, and screen location. The investigation showed that the screens, when properly placed, lower the noise level in the area downstream of the jet exit and increase it upstream.