Abstract: The thermal distortion of a Y-shaped hafnium control rod heated by arrays of individually controlled radiation heaters was studied. The large axial and radial temperature gradients specified for this control rod were easily obtained with the radiation-heating method. The distortion, as measured with dial indicators, amounted to a 2-mil movement of the free end of the rod in the direction of the coolest blade.

Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.

"Characteristics of a pulsed, occluded-gas ion source, operating in a magnetic field, have been investigated. Mass spectra of hydrogen- and deuterium-loaded sources are presented. Constructional details of the source and its operating characteristics are discussed."

This report analyzes two high-current linear accelerators, the A-54--a 48.5 megacycle resonant cavity accelerator--and the A-48, that is under construction during the time this report is written.

The change in the simple [formula] distribution of neutrons in a spherical lump of uranium caused by the distribution in velocities of thermal neutrons is calculated. If the calculated curve is fitted as well as possible by a simple [formula] curve, it is shown that the value of [formula] obtained in this way is a function of [formula], the radius of the sphere. For small radii the [formula] obtained in this manner will be as much as 25% greater than the [formula] corresponding to average velocity neutrons. The change in the thermal utilization caused by the distribution in velocities is discussed. The flux of neutrons into a sphere is calculated taking into account the velocity distribution and this is compared with the usual theory.

Report presenting the status of oscillating air forces, including forces, moments, and their respective phase angles for a 45 degree swept wing of aspect ratio 2 and for two bodies of revolution. Derivatives based on available analyses were also demonstrated for those three configurations.

"The flow-field characteristics around a swept-wing airplane model at low subsonic speed are described, and the loads induced on a typical missile model while operating within these flow fields are presented. In addition, theoretical flow fields are compared with experiment and are used in first-order estimations of the resulting induced missile loads" (p. 1).

"From these preliminary wind-tunnel tests of interceptor missile configurations and the analysis of point defense against ballistic missiles, it is concluded that adequate aerodynamic lift is readily available and should be utilized when operating under high-dynamic-pressure conditions and that more work should be done on controls, either aerodynamic or reaction type, so that the configurations may be trimmed to the angles of attack required to develop the necessary turning force" (p. 5).

"An investigation of forced-convection heat transfer and associated pressure drops was conducted with air flowing through electrically heated Inconel tubes having various degrees of square-thread-type roughness, an inside diameter of 1/2 inch, and a length of 24 inches were obtained for tubes having conventional roughness ratios (height of thread/radius of tube) of 0 (smooth tube), 0.016, 0.025, and 0.037 over ranges of bulk Reynolds numbers up to 350,000, average inside-tube-wall temperatures up to 1950deg R, and heat-flux densities up to 115,000 Btu per hour per square foot" (p. 1).

Results obtained with three different burner configurations in a connected-pipe investigation of a 16-inch ram jet are presented. The radial position of the fuel injector and the engine-outlet area both affected burner performance. For a given configuration, only slight changes in total-pressure ratio across the combustion chamber were obtained over the complete range of operation. With one burner, combustion efficiencies obtained at a combustion-chamber-inlet static pressure of 800 pounds per square foot absolute were greater than those obtained at 1920 pounds per square foot absolute.

An investigation of the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, three sweep angles at the quarter chord line, and the NACA 65A006 section as determined through a range of Mach numbers and angles of attack.

Memorandum presenting an investigation to determine the practicability of using blade boundary-layer control in order to obtain high turning angles in a stator-blade row. The overall performance of the stage was obtained for a range of weight flows at each of three tip speeds with and without hub section. Results regarding slot configuration, overall performance, and stator-blade wakes are provided.

Report presenting design features for the instrumentation used in a study of the transient performance of gas-turbine engines and control systems. The dynamic characteristics of the instrumentation are discussed and examples of typical acceleration data for a controlled and an uncontrolled engine are provided.

From Introduction: "The present report is intended to give a qualitative picture of the operation of each stage of a multistage compressor over a range of actual operating conditions from 50 to 100 percent design speed and to point out some means of achieving improved off-design performance. The method used in the report is primarily analytical and is based on single-stage-performance results."

Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.

Report presenting statistical measurements of landing-contact conditions for 144 landings of a heavy bomber airplane during routine daytime operations at Carswell Air Force Base. Using measurements obtained by a special photographic method, sinking speeds, bank angles, rolling velocities, and horizontal speeds at the instant before contact were evaluated and analyzed.

Report presenting an analysis of some strain-gage measurements of the loads carried by the wing and horizontal tail of a Boeing B-47A airplane during gradual-turn maneuvers for a variety of altitudes and Mach numbers. Results regarding the wing-load center of pressure, component loads, component-force coefficients, and fraction of the wing-fuselage load carried by the wing are provided.

"This report presents some of the theory of operation of the Mirror Machine, and summarizes the experimental work which has been carried out...The modus operandi of the Mirror Machine is to create, heat and control a high temperature plasma by means of externally generating magnetic fields."

"Dust and gas masks and respirators have been an effective method under certain environmental conditions to reduce the inhalation of toxic aerosols. Under many conditions, however, their efficacy has been seriously questioned. It is the purpose of this study to evaluation over-all respirator performance on fine aerosols and to develop equipment whereby a greater degree of respiratory protection may be assured with reliability for highly toxic atmospheres."

Early in the design of the Mark I accelerator it was decided to install magnetic lenses in the drift tubes. A number of model magnets were constructed and tested to determine the best design for these lenses. This report includes only the results of the tests on the final models of the magnets that are designed for Mark I.

Report containing ongoing projects and experiments undertaken by the Oak Ridge National Laboratory's Molten-Salt Reactor Program.

Report issued by the Oak Ridge National Laboratory discussing radiation corrosion studies. As stated in the introduction, "the purpose of this experiment was to compare the performance of a large number of materials under similar irradiation and exposure conditions" (p. 1). This report includes tables, illustrations, and photographs.

The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.

From Summary: "Estimates of the static stick-fixed stability and control characteristics of the Consolidated Vultee model 240 airplane are presented in this report. The estimates are based on tests of a 0.092-scale powered model in the 10-foot wind tunnel of the Guggenheim Aeronautical Laboratory of the California Institute of Technology. Results of the analysis are evaluated in terms of the Army specifications for stability and control characteristics which are more specific and, in general, equal to or more rigid than the Civil Aeronautics Administration requirements."