Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowable center-of-gravity travel are provided.

Abstract: "Blacosolv, trichloroethylene, is used in degreasing uranium metal. Tests were made under possible industrial conditions to determine whether a hazardous reaction between uranium and Blacosolv could occur. Temperature-rise measurements showed that there was no reaction of the metal, in various states of subdivision, with Blacosolv at temperatures up to 850 F. However, a reaction was observed in tests under which the finely divided metal, wet with solvent, was subjected to a severe impact."

Summary: The Lost Creek schroeckingerite deposit in Sweetwater County, Wyo., has attracted attention in the past both as an occurrence of comparatively rare minerals and more recently as a possible source of uranium ore. During the summer of 1948 a newly-formed company by the name of Uranium, Inc., explored part of the deposit by bulldozer trenching and drilling. under the technical direction of the Minerals Engineering Company of Grand Junction, Colo. Examination of the significant exposures of the schroeckingerite deposit indicated that the uraniferous beds are discontinuous and that their areal distribution is erratic. The overburden has an average thickness of 2.5 feet.

The report summarizes results obtained since September, 1951, by total neutron yield experiments using 190 Mev deuterons and the MnSo4 tank method (UCRL-1375 and UCRL-1480). A new method of beam monitoring has resulted in establishing firmly the absolute yield for solid uranium and thorium primary targets backed by a solid uranium secondary. The beam monitoring was done by using a primary target built into a faraday cup. This method circumvents errors caused by recombination in the ionization chambers used previously.

Report discussing an investigation into several types and sizes of flaps and spoilers located forward of the elevators on the upper surface of the horizontal stabilizer of a model of a radial-engine pursuit airplane. Information about the elevator characteristics, elevator-fixed and elevator-free balance lift coefficient, and trim drag coefficient for a range of Mach numbers is provided.

Memorandum presenting an investigation in the supersonic pressure tunnel at a free-stream Mach number of 2.01 and at angles of attack up to 15 degrees of the static pressures and boundary-layer characteristics on the forward parts of nine fusleages of various cross-sectional shapes. Results regarding the static pressure distributions, boundary-layer characteristics, and selection of fuselage shapes for use with top-mounted scoop inlets are provided.

Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.

Report presenting tests at Mach numbers between 1.36 and 2.01 of a twin-scoop air intake enclosing 61.5 percent of the maximum circumference of a body of revolution and located five forebody diameters behind the apex, which showed that the total pressure recovered after diffusion was about 10 percent greater than that attained in previous tests with an annular entrance of the same area.

Report presenting the results of tests on a model of a jet-propelled airplane and a comparison of drag, maximum lift coefficient, and elevator angle required for level flight in the wind tunnel and in flight. Results regarding the aerodynamic characteristics, longitudinal control, wing pressure distribution, and dive-recovery flaps are provided.

From Introduction: "This report presents the aerodynamic characteristics at low speed end high Reynolds number as determined in the Ames 40- by 80 foot wind tunnel."

Report presenting an investigation of a 24-inch-diameter rotor for a supersonic axial-flow compressor in air up to an actual tip speed of 1654 feet per second and a maximum equivalent tip speed of 1765 feet per second. Results regarding overall performance, rotor-inlet characteristics, rotor-passage flow characteristics, and rotor-outlet characteristics are provided.

Report presenting an investigation to determine the effect of leading-edge chord-extensions on high-lift pitching moment and performance characteristics at subsonic and transonic speeds. Three models with the same wings were used. Results regarding low-speed development and high-speed characteristics are provided.

Report presenting measurements of the local total pressures and flow-deflection angles in the flow field of a body and a canard-type control-surface combination at a rearward fuselage station which corresponded to a possible engine inlet location. The survey showed large total-pressure losses in the wake of the control surface and a shift in the circumferential distribution of the boundary-layer air about the fuselage due to deflection of the control surface.

Report presenting approximate methods of analysis applied to the estimation of the normal force and pitching moment of the body and the wing-body and tail-body combinations of an air-to-air missile and to the estimation of the same characteristics of the the complete configuration. Results regarding the isolated body, wing-body combination, tail-body combination, and the complete configuration are provided.

Report presenting an experimental investigation of the effects of a horizontal tail in various vertical positions on the longitudinal stability characteristics of a wing-fuselage combination of 45 degrees sweepback and aspect ratio 8 in the 19-foot pressure tunnel. Testing occurred at two wing incidence angles and various high-lift and stall-control devices at a specified Mach and Reynolds number. The horizontal tail was tested at four vertical positions.

Report presenting aerodynamic characteristics in steady roll on a complete model and its component parts. The model consisted of a wing and horizontal tail with a 45 degree sweepback at the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding rolling moment due to rolling, yawing moment due to rolling, and lateral force due to rolling are provided.

The free turbulent mixing of a supersonic jet of Mach number 1.6 has been experimentally investigated. An interferometer, of which a description is given, was used for the investigation. Density and velocity distributions through the mixing zone have been obtained. It was found that there was similarity in distribution at the cross sections investigated and that, in the subsonic portion of the mixing zone, the velocity distribution fitted the theoretical distribution for incompressible flow. It was found that the rates of spread of the mixing zone both into the jet and into the ambient air were less than those of subsonic jets.

Report presenting flight testing of a scale rocket-propelled model of the Convair XF2Y-1 airplane with open ducts and elevons deflected upward 3.5 degrees through a range of Mach numbers. Report presenting lift and stability, drag, and duct flow are provided.

Report presenting an investigation to determine the effects of altitude and inlet-pressure distortions on the steady-state and surge characteristics of the J57-P-1 two-spool turbojet engine in the altitude wind tunnel. Steady-state performance and surge fuel flows were obtained with a uniform inlet distribution at a range of altitudes at flight Mach number 0.8.

Various flow visualization results at a nominal Mach number of 5 are presented for cylindrically blunted, unswept and 60-degree swept fins with and without small clearance gaps, partially immersed in a turbulent boundary layer of about 2.6 inches thickness. In addition, pressure and heat transfer measurements were obtained on the flat plate upon which the fin was mounted. Oil smear, azobenzene and Schlieren flow visualization tests were made.

This report deals with the (1.1) physical properties of graphite, (1.2) effects of pile irradiation on the properties of graphite, (1.3) effect of irradiation on "ceramic" materials, (1.4) effects of radiation on ice -- the x-ray induced luminescence of ice, (1.5) investigation of color centers and other optical properties of single crystals. (2.1) radiation chemistry of liquids, (2.2) application of mass spectrometry to chemical problems, (2.3) vapor pressure and heat of vaporization of uranium, (3.1) nuclear properties of Zr93 and Nb93m from fission, (3.2) mass distribution in the spontaneous fission of Cm242, (3.3) Upper limit to the lifetimes of the first excited states of Th236, U234, and Pu236, (3.4) on the one-body model of alpha radioactivity, (4.1) spectrographic analysis, (4.2) chemical analysis, (5.1) paramagnetic resonance measurements, and (5.2) the 60-inch cyclotron.

In H measurements, the measured flux-linkage change represents twice the value of H to be plotted. In B measurements the bucking coil links flux equal to the air-flux in the B-measuring coils. The measured flux change therefore corresponds to twice the flux of intrinsic magnetization in the sample.

From abstract: "Rats have been fed active strontium which was adsorbed on clay, while their controls were fed the same amount of active strontium in aqueous solution. There was no significant difference in the amount deposited in the skeleton between the two groups, and it is concluded that if ions are adsorbed on inert material, they will be eluted during their passage through the gastrointestinal tract."

This report is a comparative cost study of radioactive waste disposal for the Lawrence Radiation Laboratory (UCRL). In particular, it compares the costs of sea disposal in depths of 1000 fathoms and of 2000 fathoms off the California coast with land burial of the wastes at the Hanford Atomic Products Operation (HAPO), Richland, Washington, at the National Reactor Testing Station (NRTS), Idaho Falls, Idaho, or at the Nevada Test Site (NTS), Nevada. In the comparison, the cost of utilizing a commercial waste-disposal firm is also shown as well as a tentative cost of using the Military Sea Transport Service (MSTS).