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."

Abstract: The design and construction of a slide rule for calculating the solid angle subtended by a rectangle at a point located on a line perpendicular to the center of the rectangle are described.

Abstract: "The results obtained from the tests conducted for the purpose of determining the corrosivity of a 30 percent-solution of uranyl fluoride to various metals indicate that stainless steels (type 302, 304, 321 and 316) have very good resistance; while monel, nickel and aluminum, respectively, exhibit diminishing resistance. Stainless steel, type 316, was the most resistant of the specimen tested."

"A technical method is given for calculating the axial interference velocity of a propeller. The method involves the use of certain weight functions P, Q, and F. Numerical values for the weight functions are given for two-blade, three-blade, and six-blade propellers" (p. 53).

"The problems associated with propeller noise and with the design of propellers that are less noisy than those conventionally used are presented. Three aspects of these problems are discussed: acoustical, aerodynamic, and structural. Some of the factors which must be considered in the design of a quiet propeller are outlined" (p. 1).

Report presenting an investigation conducted to determine the effects of increased gas temperatures on the performance of cast Vitallium blades in a turbojet engine. Results regarding the experimental investigation and metallurgical investigation are provided.

Report presenting measured pressure over airfoils at Mach number 1, with subsonic velocities at the nose and supersonic velocities throughout the rear portion, are analyzed by comparison with calculations for similar cases. Results regarding the theoretical basis of approximation, comparison of Prandtl-Meyer flow with measurements, comparison of linear-velocity extrapolation with measurements, and effect of boundary layer upon airfoil pressures are provided.

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.

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.

Report discussing the effect of the proximity of the ground on the stability and control characteristics of a vertically rising airplane model in the hovering condition. The dynamic behavior of the model in take-offs and landings and when it was hovering near the ground was also investigated. Force tests to determine the change in the vertical-tail yawing moments with control deflection and with angle of yaw for various heights were also conducted.

Experimental investigation was conducted at Mach number 1.88 to determine performance characteristics of half a 50 degree-conical-spike inlet mounted on a flat plate. Initial boundary layer was removed up-stream of inlet by a ram-type scoop of variable height. Initial boundary-layer thickness was also varied. With complete removal of initial boundary layer, total-pressure recovery of approximately 70 percent. Several alternative boundary-layer-removal systems were investigated which decreased the adverse effect of operating the ram scoop sub-critically.

Report presenting data obtained in flight using a schileren apparatus that photographed the shock-wave interaction with a thick turbulent boundary layer on a wing. Local Mach number and boundary-layer characteristics obtained from pressure measurements in the vicinity of the shock wave are also presented.

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.

Report presenting an experimental investigation of the aerodynamic characteristics of a fin-stabilized body of revolution, designated as RM-10, in a supersonic wind tunnel. Pressure distributions and force characteristics were determined at two different Mach numbers. Results regarding pressure distributions, body-alone force tests, and body-tail combination force tests are provided.

Report presenting longitudinal frequency-response characteristics of a 35 degree swept-wing airplane computed from flight measurements. Also presented are pitching-velocity frequency responses to displacements of the adjustable stabilizer. Results regarding frequency-response curves, transfer functions, elevator effectiveness, altitude variations, and potential errors in data are provided.

"A theoretical investigation has been made to determine the effect of nonlinear stability derivatives on the lateral stability of an airplane. Motions were calculated on the assumption that the directional-stability and the damping-in-yawing derivatives are functions of the angle of sideslip. The application of the Laplace transform to the calculation of an airplane motion when certain types of nonlinear derivatives are present is described in detail" (p. 1009).

Report presenting an investigation to obtain forced-convection heat-transfer and pressure-drop data for flow of air between electrically heated parallel flat plates stacked to form passages of short length-to-effective-diameter ratio. The primary purpose of the investigation is to determine the interference effects of the upstream stack of plates on the heat-transfer and friction characteristics of the downstream stack. Results regarding the plate temperature gradients, heat-transfer data, and friction data are provided.

In order to provide engineers interested in rotating-wing aircraft, but with no specialized training in stability theory, some understanding of the factors that influence the flying qualities of the helicopter, an explanation is made of both the static stability and the stick-fixed oscillation in hovering and forward flight in terms of fundamental physical quantities. Three significant stability factors -- static stability with angle of attack, static stability with speed, and damping due to a pitching or rolling velocity -- are explained in detail.

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.

From introduction: "This conference represents the first attempt by a project-wide group of scientists and engineers to collaborate on the problem associated with the planning and design of "Hot" Laboratories. The idea, as originally conceived by Dr. W. E. Winsche, was to discuss some general and perhaps some specific aspects of "Hot" Laboratory design with a small group of interests individuals from various sites."

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

Report presenting an investigation to determine the static longitudinal and lateral stability characteristics of a model of X-1E airplane at combined angles of attack and sideslip. Results regarding the static longitudinal and lateral force and moment characteristics and stability derivatives are provided.

Report presenting the results of an investigation to determine the effects of full-span trailing-edge flaps on the static longitudinal characteristics of a triangular wing-body combination. Data was obtained for the basic configuration and for a wing with the control surfaces deflected for longitudinal control.

Report presenting a rocket-powered free-flight model of an interceptor-type airplane with an overhanging tail boom with the jet on and off at a range of Mach numbers. Results regarding longitudinal trim, drag, and lift are provided.