Report presenting an investigation of the aerodynamic loading characteristics of a wing-fuselage combination in the slotted test section of the transonic tunnel. The test was part of a systematic investigation of the effects of varying the amount of sweepback on wings in order to determine their suitability for transonic flight. Results regarding span load characteristics, normal-force characteristics, wing-tip angle of twist, spanwise distribution of section pitching-moment coefficient, pitching-moment characteristics, and fuselage characteristics in presence of wing are provided.

Abstract: Information on five uranium binary alloy systems has been surveyed. These systems are the alloys of uranium with zirconium, chromium, columbium, vanadium, and molybdenum. The equilibrium diagrams are discussed, and where available, data have been included on diffusion studies, cladding experiments, and mechanical properties.

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From Introduction: "The purpose of this report is to compare the effect on engine performance of the variable-area exhaust nozzle for axial- and centrifugal-flow turbojet engines."

From abstract: "A continuous countercurrent solid-liquid contactor has been developed which retains the desirable features of the conventional fixed bed and gains the advantages of countercurrent flow. It can be adapted to many solid-liquid mass-transfer processes such as ion exchange, silica gel adsorption, and ore leaching."

The chain reacting conditions for plutonium nitrate in water solution have been examined experimentally for a variety of sizes of spheres and cylinders. The effects on the critical mass of the displacement of hydrogen and the addition of poisons to the fuel were measured in water tamped and bare reactors. In this report the data obtained in the investigation is presented graphically and in tables. Some preliminary analysis has been made yielding the results: (i) the absorption cross-section of Pu{sup 240} is 925 {plus_minus} 200 barns and (ii) the minimum critical mass of Pu{sup 239} in water is 510 grams at concentration of about 33 grams per liter.

An estimated minimum critical mass for each of the process vessels in the 231 Building has been calculated on the basis of critical mass data given in the P-11 Project Document HW-24514. The calculations are made assuming the plutonium to be a homogeneous mixture of precipitate and water with some slight neutron poisoning due to other elements. The precipitate is further assumed to have partially settled making an effectively infinite water reflector above the plutonium and hence reducing the critical mass.

Report presenting the design of a mixed-flow impeller with special emphasis on the reduction or elimination of velocity deceleration along the wetted surfaces, especially the blade suction surface. With the use of a provisional hub-shroud profile, the blade shape at the blade mean height was determined from a prescribed velocity distribution.

An investigation was conducted to determine the performance characteristics of a mixed-flow impeller which was designed with special emphasis on the reduction or elimination of flow decelerations along wetted surfaces. The performance was investigated over a range of equivalent impeller speeds from 700 to 1600 feet per second and over a range of flow rates from maximum adiabatic temperature-rise efficiency, measured at 1-1/2 impeller diameters in a vaneless diffuser, at the design speed of 1400 feet per second were 4.00 and 0.83, respectively.

From Summary: "Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9."

Report presenting an attempt to improve the part-speed weight-flow-range characteristics of a typical inlet stage by two different approaches. Results regarding the effects of reduction in camber and effects of reduction in guide-vane turning are provided.

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Report presenting an investigation of an axially symmetric spike-type nose inlet suitable for a nacelle power-plant installation in the 8- by 6-foot supersonic tunnel at a range of Mach numbers and angles of attack. The inlet was designed to attain a mass-flow ratio of unity a Mach number 2.0. Results regarding the performance of inlet A and inlet B, which differed based on subsonic diffuser area variation, are provided.

Indenter gages, Wiancko gages, and interferometer gages were used to measure air overpressure vs time at essentially ground level stations for both the surface (S) and undprground (U) atomic explosions. For the S Burst several instruments were placed on a line extending from an overpressure region of 13 psi to a region of less than one psi. The air measurements for the U Burst ranged from 32 to 2 psi. (D. L.G.)

Report presenting rocket-propelled models flown at transonic and supersonic speeds to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a sweptback wing. Results regarding the total drag coefficient, wing-plus-interference drag coefficients, and force-break Mach number are provided.

This report follows and discusses an experimental investigation of gamma-induced light production in water, focusing on the establishment of the mechanism of the light production process and the measurement of the radiant flux associated with a gamma-ray source placed in water.

This report follows a manuscript report made in January 11, 1952, and provides results of a survey that gives corrections as well as suggestions for new and local sources of aggregate material in comparison to the original report. These reports were made in response to a heavy desire of improvement in reactor design and shielding.

Report documenting the ongoing research and developments of the Oak Ridge National Laboratory's Homogeneous Reactor Project.

High energy p-p scattering has been interpreted by several authors in terms of highly singular noncentral interactions. The triplet state calculations were carried out in the Born approximation and, together with the singlet, yielded an almost isotropic (c.m. system) differential cross section. Agreement with experiment was good at large angles but the theoretical peak in the forward direction, due mostly to singlet d scattering, was too large. It is not clear however that the Born approximation should be valid for singular potentials.

Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.

Report presenting an investigation of whether or not a two-stage turbine with the frontal area no larger than the compressor frontal area could be satisfactorily designed to drive a particular compressor under take-off conditions. The low blade-tip speed, high work, and high air flow per unit of frontal area of the compressor make it critical that a two-stage turbine is designed to drive it. Results regarding the effect of work division, effect of variation in cone angle, and effects of radial variations on velocity diagrams are provided.

Abstract: "The transformation of metastable beta uranium crystals was found to proceed by a martensitic reaction at room temperature. The features of the transformation of particular interest were that individual uranium martensite plates formed isothermally and grew at a slow rate isothermally."

From abstract: "This report presents the laboratory development of the MTR-RaLa Process for the production of barium140 from Materials Testing Reactor assemblies." The laboratory studied four possible chemical schemes with the final process being chosen "on the basis of chemical yield and purity of product, ease of recovery of uranium235, simplicty of equipment, and overall time required for processing" (from introduction).

Report presenting an investigation to determine the directional characteristics of a sharp-nosed fuselage through a large angle-of-attack range at zero angle of sideslip. The fuselage was found to experience a large increase in yawing moment as the angle of attack increases. The results also indicated that a ring or other roughness used on the nose caused a large decrease in the yawing moment obtained at high angles of attack.